Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 1 of 182

Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2281

Original Issue: December 13, 2007

Revision 1: November 25, 2009

ATA System: 2817 2831

SUBJECT: FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps 

- Change to Give Redundant Control of the Fuel Pumps

BOEING PROPRIETARY, CONFIDENTIAL, AND/OR TRADE SECRET

Copyright © 2007 The Boeing Company

Unpublished Work - All Rights Reserved

Boeing claims copyright in each page of this document only to the extent that the page contains copyrightable 

subject matter. Boeing also claims copyright in this document as a compilation and/or collective work.

This document includes proprietary information owned by The Boeing Company and/or one or more third 

parties. Treatment of the document and the information it contains is governed by contract with Boeing. For 

more information, contact The Boeing Company, P.O. Box 3707, Seattle, Washington 98124.

Boeing, 707, 717, 727, 737, 747, 757, 767, 777, BBJ, BOEING BUSINESS JET, DC-8, DC-9, DC-10, MD-10, 

MD-11, MD-80, MD-90, the Boeing logo and the Boeing livery are among the trademarks owned by Boeing or 

its subsidiaries. No intellectual property license (express or implied) is granted in connection with this document 

or otherwise.
 BLANK PAGE

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BOEING SERVICE BULLETIN 747-28A2281

BLANK PAGE
 Table of Contents

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

Table of Contents

Revision Transmittal Sheet . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 5

Summary . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9

1. PLANNING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

A. Effectivity . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

1. Airplanes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 13

2. Spares Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

B. Concurrent Requirements . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

C. Reason . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 25

D. Description . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 26

E. Compliance. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

F. Approval . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

G. Manpower . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 27

H. Weight and Balance Changes . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

I. Electrical Load Data . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 44

J. References . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

1. Existing Data: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 45

2. Data supplied with this Service Bulletin: . . . . . . . . . . . . . . . . . . . . . . . . . 45

3. Installation Drawings Used in the Preparation of this Service Bulletin: . . . . . . . . . . 46

K. Publications Affected . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 46

L. Interchangeability and Intermixability of Parts . . . . . . . . . . . . . . . . . . . . . . . . . 47

2. MATERIAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

A. Material - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 49

B. Industry Support Information . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

C. Parts Necessary For Each Airplane . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

1. Kits/Parts: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 50

2. Parts and Materials Supplied by the Operator: . . . . . . . . . . . . . . . . . . . . . . 56

3. Parts Modified and Reidentified: . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

4. Parts Removed and Not Replaced: . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

D. Parts Necessary to Change Spares . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

E. Special Tooling - Price and Availability. . . . . . . . . . . . . . . . . . . . . . . . . . . . . 56

F. Special Tooling Necessary to do this Service Bulletin . . . . . . . . . . . . . . . . . . . . . 56

3. ACCOMPLISHMENT INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

A. GENERAL INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

B. WORK INSTRUCTIONS . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 57

FIGURE 1: INSTALL RELAYS ON E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 82

FIGURE 2: WIRE BUNDLE ROUTING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . . . 92

FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 96

FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 97

FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . . . . . . . 98

FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 99

FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . . . 101

FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . . 103

FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . . 104

FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 106

FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 108
 Table of Contents

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Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . 110

FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . 112

FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758) . . . . . . . . . . . . . 113

FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 114

FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 116

FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 118

FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 120

FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 122

FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 123

FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 124

FIGURE 22: INSTALL RELAYS ON E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . . . 126

FIGURE 23: WIRE BUNDLE ROUTING INFORMATION . . . . . . . . . . . . . . . . . . . . . . . 133

FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 137

FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . 138

FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . 139

FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758) . . . . . . . . . . . . . . . . . . . . 140

FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 141

FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 143

FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 144

FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 146

FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . . . . . . . . 148

FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 149

FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . 151

FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE . . . . . . . . . . . 154

FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF . . . . . . . . . . . . . . . . . . . . . . . . . . 162

FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 165

FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 166

FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 167

FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488) . . . . . . . . . . . . . 169

FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 171

FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851) . . . . . 173

FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851) . . . . . . . . . . . . . 175

FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . . . . . . . 176

FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 177

FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588) . . . . . . . . . . . . . . 179

FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845) . . . . . . . . . . . . . . 181
Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 5 of 182

Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2281 Revision Transmittal Sheet

Original Issue: December 13, 2007

Revision 1: November 25, 2009

ATA System: 2817 2831

SUBJECT: FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps 

- Change to Give Redundant Control of the Fuel Pumps

This Revision includes all pages of the service bulletin.

COMPLIANCE INFORMATION RELATED TO THIS REVISION

No more work is necessary on airplanes changed as shown in the original issue of this service bulletin.

REASON FOR REVISION

This revision is sent to address the comments received from operators since the original issue of the service 

bulletin and incorporate differences identified during the validation of the service bulletin.

Airplanes RT966-RT967 were deleted from the effectivity. These airplanes are not equipped with horizontal 

stabilizer fuel tanks.

As a part of a service bulletin validation program, this change was completed on Airplane RT409 by original 

issue of Service Bulletin 747-28A2281 and before the release of Revision 1 of this service bulletin. The change 

completed on airplane RT409 by Service Bulletin 747-28A2281 is equivalent to Revision 1 of this service 

bulletin. Airplane RT409 has the configuration of a Group 20 airplane.

The following effectivity group assignments were changed to show the correct wiring configuration for the 

affected airplanes. New airplane Groups 20-37 were added to the service bulletin. The table below shows the 

new Groups assignments for the effective airplanes:

Airplanes Affected Old Airplane Group New Airplane 

Group

RT061, RT407-

RT410, RT480-

RT487

2 20

RT431-RT435 2 21

RT436 2 22

RT573-RT574, 

RT576

17 23

RT501, RT506-

RT507, RT509

4 24

RT455 2 25
 

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BOEING SERVICE BULLETIN 747-28A2281

The following sections of the service bulletin are changed:

— ATA system - added ATA 2817

— Summary Section, Group and Configuration tables in Section 1, added new airplane Groups 20-37 where 

applicable.

— Concurrent Requirements, updated revision level for service bulletin 747-28A2262.

— Compliance statements in the Summary and Planning sections were revised with wording "original issue 

date".

— Description Section 1.D added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Manpower tables revised to add new airplane Group 20-22; Group 23, Configuration 2; Group 24-37 and 

new figures 37-47 to man-hour tables.

— Weight and Balance added new airplane Groups 20-37 to the table and new weight and balance 

information for airplane Groups 16; Group 18; Groups 32-37.

— Electrical Load Data added new airplane Groups 20-37 to the applicability.

— Material Information Section 2, Added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37 

to 015U1808-1 Top Kit. Created new supplemental kit 015U1808-3 with new connector for Group 16; 

Group 18, Configuration 2; Groups 32-37 airplanes. Figure kits were updated with new applicability and 

new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Parts and Materials, Supplied by the operator, added washer and nut for alternate tray configuration.

— Accomplishment Instructions Section 3, General Information, added Note 7 to clarify wire clamp size 

selection.

RT503, RT505 2 26

RT451-RT454 2 27

RT021-RT022 2 28

RT001-RT005, 

RT401-RT406, 

RT471-RT479, 

RT571

2 29

RT502, RT504 2 30

RT551-RT556, 

RT591, RT641, 

RT643-RT645, 

RT671, RT691-

RT692

2 31

RM081, RM083, 

RT411-RT412, 

RT609-RT630, 

RT753-RT755, 

RT945-RT949

1 32

RT605-RT608, 

RT752

2 33

RM146, RT783-

RT784

8 34

RT777 11 35

RT751 2 36

RT601-RT604 2 37

Airplanes Affected Old Airplane Group New Airplane 

Group
 

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BOEING SERVICE BULLETIN 747-28A2281

— Accomplishment Instructions Section 3. revised figure reference, airplane applicability and added new 

airplane Group 20-22; Group 23, Configuration 2; Group 24-37 where applicable.

— Figure 1 changes: 

— Added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Revised sheet 1 and 2, added sheets 5, 6 and 7 to show alternate tray configuration.

— Revised Circle Note 2, More Data, added additional wording, If Static Inverter is installed.

— Revised Circle Note 3, More Data, added information for bolt installation if equipment tray has 

stiffening joggle.

— Revised Circle Note 6, More Data, added hole diameter to drilling procedure.

— Revised Circle Note 18, More Data, added additional wording, If Static Inverter was removed.

— Added Note (e), gives information for bracket and bolt installation if equipment tray has stiffening 

joggle.

— Figure 2 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Figure 3 Flag Note 2, corrected SWPM call out. Changed SWPM 20-10-11 to SWPM 20-61-11 and added 

new airplane Group 32, 34-35.

— Figures 4 revised illustration to show wire W4488-071-22 as a cap and stowed wire.

— Figures 5 revised airplane applicability.

— Figures 6 revised airplane applicability and added new airplane Group 30-31, 33, 37.

— Figures 8 revised airplane applicability and added new airplane Group 20-22; Group 23, Configuration 2; 

Group 24-31.

— Figures 10 revised airplane applicability.

— Figure 13 revised Flag Note 2 socket P/N to BACC47CP1S for connector D41807J. Revised airplane 

applicability and added new airplane Group 20-22; Group 23, Configuration 2; Group 24-31.

— Figure 14 revised to show wire W4758-633-24 connected to pin C9 on connector DW3417C and wire 

W4758-634-24 connected to pin C8 on connector DW3417C. The nomenclature shown inside M7952 is 

also revised to show "FUEL CMD STAB R" for pin C9 and "FUEL CMD STAB L" for pin C8. Added new 

airplane Group 20-22; Group 23, Configuration 2, Group 24-37.

— Figure 15 added new airplane Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36.

— Figure 16 and 17 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Figure 18 revised Flag Note 2 socket P/N to BACC47CP3T for connector D40106J and added new airplane 

Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36.

— Figure 19 revised airplane applicability and added new airplane Group 20-22, 29.

— Figure 20 revised airplane applicability and added new airplane Group 30-35, 37.

— Figure 21 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— Figure 26 revised Flag Note 2 socket P/N to BACC47CP1S for connector D41807J.

— Figure 27 revised to show wire W4758-633-24 connected to pin C9 on connector DW3417C and wire 

W4758-634-24 connected to pin C8 on connector DW3417C. The nomenclature shown inside M7952 is 

also revised to show "FUEL CMD STAB R" for pin C9 and "FUEL CMD STAB L" for pin C8.

— Figure 31 revised Flag Note 2 socket P/N to BACC47CP3T for connector D40106J.

— Figure 36 added new airplane Group 20-22; Group 23, Configuration 2; Group 24-37.

— New Figure 37 added to use pin 30 on connector D40103P for Group 20, 29 airplanes.

— New Figure 38 added to use pin 36 on connector D40103P for Group 6, Configuration 2; Group 23, 

Configuration 2; Group 24 airplanes.

— New Figure 39 added to use pin 30 on connector D40103P for Group 3, Configuration 1; Group 21-22 

airplanes.

— New Figure 40 added to use pin 36 on connector D40103P for Group 5, Configuration 2, Group 13, 25-28, 

36 airplanes.

— New Figure 41 added to show wire W3851-320-12B deleted from pin B2 and wire W3851-321-12Y deleted 

from pin C2 on relay R7401 for Group 19, Configuration 1; Group 21, 26-27, 29-31, 37 airplanes.

— New Figure 42 added to show wire W3851-323-12B deleted from pin B2 and wire W3851-324-12Y deleted 

from pin C2 on relay R7402 for Group 21, 26-27, 29-31, 37 airplanes.

— New Figure 43 added to use pin 36 on connector D40103J for Group 5, Configuration 2; Group 6, 

Configuration 2; Group 13; Group 23, Configuration 2; Group 24-28, 36 airplanes.
 

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BOEING SERVICE BULLETIN 747-28A2281

— New Figure 44 added to install new connector D41785P for Group 18, Configuration 2; Group 32-33, 36-

37 airplanes.

— New Figure 45 added to install new connector D41785P for Group 16, 35 airplanes.

— New Figure 46 added to install new connector D41785P for Group 34 airplanes.

— New Figure 47 added to install new connector D41785J for Group 16; Group 18, Configuration 2; Group 

32-37 airplanes.

The data given in Information Notice 747-28A2281 IN 01, IN 02 and IN 03 is included in this revision.

Paragraph 1.A., Effectivity, shows changes of airplane operators. Each operator should examine the Effectivity 

paragraph for changes.

Vertical lines are put on the left edge of each page, except in Paragraph 1.A., Effectivity, to show the location 

of important changes.

Pages with no vertical lines have no important changes.

REVISION HISTORY

Original Issue: December 13, 2007

Revision 1: November 25, 2009
Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 9 of 182

Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2281 Summary

Original Issue: December 13, 2007

Revision 1: November 25, 2009

ATA System: 2817 2831

SUBJECT: FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps 

- Change to Give Redundant Control of the Fuel Pumps

CONCURRENT REQUIREMENTS

Refer to Paragraph 1.B. for the list of concurrent requirements.

BACKGROUND

Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel tank as a 

result of a horizontal stabilizer override/jettison fuel pump that continues to run after it has been commanded 

off. An ignition source in a fuel tank could result in a fire or an explosion. 

A safety assessment conducted by Boeing indicates that there is a small risk of an ignition source in a fuel tank 

if a horizontal stabilizer override/jettison fuel pump continues to run for an extended time after fuel level goes 

below the pump inlet. Normally the pump is commanded off when a low fuel pressure is indicated. If a single 

failure in the pump control circuitry occurs, a pump can continue to run after it is commanded off. When a pump 

runs after the fuel level goes below the pump inlet, there is a small risk that the pump can cause an ignition 

source in the fuel tank from an overheat condition, electrical arcs or frictional sparks. 

This service bulletin gives the instructions to install new relays and wiring in the circuitry for the horizontal 

stabilizer override/jettison fuel pumps. The new relays and wiring for the horizontal stabilizer override/jettison 

fuel pumps remove power from these pumps when the pumps continue to run after the pumps have been 

commanded off. Each set of relays have a new Engine Indication and Crew Alerting System (EICAS) status 

message to annunciate a fault in a pump control relay. For the horizontal stabilizer tank, the EICAS status 

messages are FUEL CMD STAB L and Fuel CMD STAB R. These changes help make sure that the risk of an 

ignition source in a fuel tank is kept to a minimum. The changes are identical to the changes to airplanes in 

production.

This service bulletin is the result of the safety assessments conducted by Boeing under Special Federal Aviation 

Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation Requirements".

ACTION

Group 1-8, 10-15, 17, 19-31: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 

shelf. Get access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install 

new airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Rework 

wiring from P180 panel to Modularized Avionics and Warning Electronics Assembly (MAWEA) Card File (P54). 

Do a functional test. Close access.
 

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BOEING SERVICE BULLETIN 747-28A2281

Group 9: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get access and 

rework/install new airplane wiring from E8 shelf to disconnect AC1401 and install new airplane wiring from 

disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. Install new wiring from P180 

panel to MAWEA Card File (P54). Do a functional test. Close access.

Group 16, 18, 32-37: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get 

access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and rework/install new 

airplane wiring from disconnect AC1401 to P180 panel and add new connector to P180 panel. Rework/install 

new wiring on P180 panel. Rework wiring from P180 panel to MAWEA Card File (P54). Do a functional test. 

Close access.

Boeing Service Bulletin 747-28A2280 is related to this service bulletin and has some common access 

procedures.

EFFECTIVITY

747-400 Airplanes. Refer to Paragraph 1.A.1., Airplanes for the list of affected airplanes.

COMPLIANCE

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to this service 

bulletin. The Airworthiness Directive will make the compliance tasks and times given in this service bulletin 

mandatory.

Boeing recommends that this service bulletin be incorporated within 5 years after the original issue of this 

service bulletin.

INDUSTRY SUPPORT INFORMATION

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

MANPOWER

MATERIAL INFORMATION

Boeing Supplied Kits/Parts.

Refer to Paragraph 2.A., Material - Price and Availability.

Airplanes Total Task Hours Elapsed Hours

Groups 1, 7, 18, 

19, 32

101.20 52.30

Groups 2, 3, 5, 10, 

12, 14, 20-22, 25-

31, 33, 36-37

101.30 52.35

Groups 4, 6, 15, 

17, 23-24

101.10 52.25

Group 8, 11, 34-35 101.40 52.40

Group 9 107.40 55.30

Group 13, 16 101.50 52.45
 

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BOEING SERVICE BULLETIN 747-28A2281

STA

1580

STA

2200

2100

STA

STA

1980

AC1401

ADD/REWORK

2 WIRES FROM

E-8 SHELF TO

P180 PANEL

(W4588)

ADD/REWORK

2 WIRES FROM

E-8 SHELF TO

P180 PANEL

(W4488)

INSTALL 2 NEW

RELAYS ON E-8

SHELF. REWORK

WIRING ON E-8

SHELF.

REVISE WIRING

ON P180 PANEL AND

MAWEA CARD FILE P54.

1325681
 

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BLANK PAGE
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Commercial

Airplanes 747

Service Bulletin

Number: 747-28A2281

Original Issue: December 13, 2007

Revision 1: November 25, 2009

ATA System: 2817 2831

SUBJECT: FUEL - Fuel Jettison System - Horizontal Stabilizer Tank Override/Jettison Fuel Pumps 

- Change to Give Redundant Control of the Fuel Pumps

1. PLANNING INFORMATION

A. Effectivity

1. Airplanes

Refer to Service Bulletin Index Document D6-30300 Part 3 for Airplane Variable Number, Line 

Number, and Serial Number data.

This service bulletin is for the airplanes shown below. An equivalent change is on subsequent 

production airplanes. Refer to PRR 85539-8 for data about this change.

GROUP CONFIGURATION DESCRIPTION

1 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and Modularized Avionics and 

Warning Electronics Assembly (MAWEA) card 

file, Top KIt 015U1808-1 kit for parts.

2 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top kit 

015U1808-1 kit for parts.

3 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2197 or 747-

28-2183.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2197 or 

747-28-2183.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2197 or 

747-28-2183.
 

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BOEING SERVICE BULLETIN 747-28A2281

4 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

5 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2265.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2265.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2265.

6 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2272.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2272.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2272.

7 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top kit 

015U1808-1 kit for parts.

8 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top kit 

015U1808-1 kit for parts.

9 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top kit 

015U1808-2 kit for parts.

10 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top kit 

015U1808-1 kit for parts.

11 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file. Top Kit 

015U1808-1 kit of parts.

12 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

13 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

GROUP CONFIGURATION DESCRIPTION
 

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BOEING SERVICE BULLETIN 747-28A2281

14 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

15 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2275.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2275.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2275,

16 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

17 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2274.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2274.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2274.

18 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2247.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2247.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2247.

19 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2197 or 747-

28-2183.

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2197 or 

747-28-2183.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2197 or 

747-28-2183.

20 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

21 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

GROUP CONFIGURATION DESCRIPTION
 

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BOEING SERVICE BULLETIN 747-28A2281

22 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

23 - 747-400 airplanes with horizontal stabilizer tank 

affected by service bulletin 747-28-2274

1 747-400 airplanes with horizontal stabilizer tank 

changed by service bulletin 747-28-2274.

2 747-400 airplanes with horizontal stabilizer tank 

not changed by service bulletin 747-28-2274.

24 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

25 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

26 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

27 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

28 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

29 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

30 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

31 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

32 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

GROUP CONFIGURATION DESCRIPTION
 

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BOEING SERVICE BULLETIN 747-28A2281

Airplane models:

747-400

IDENTIFICATION BY CUSTOMER, CUSTOMER CODE, GROUP AND VARIABLE NUMBER

AEROLINEAS ARGENTINAS (ARG)

11 RT704

13 RT701–RT702

AIR ATLANTA ICELANDIC (AID)

1 RT515

36 RT751

AIR CARGO GERMANY (CGU)

1 RT633

AIR CHINA (BEJ)

1 RM341

AIR CHINA CARGO (CGC)

10 RT101 RT103

AIR FRANCE (AFA)

1 RM401–RM403 RT071–RT073 RT121

31 RT591

33 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

34 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

35 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

36 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

37 - 747-400 airplanes with horizontal stabilizer tank 

which require wiring changes to the E8 shelf, 

P180 panel and MAWEA card file, Top Kit 

015U1808-1 kit for parts.

GROUP CONFIGURATION DESCRIPTION
 

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BOEING SERVICE BULLETIN 747-28A2281

AIR NEW ZEALAND (ANZ)

1 RM082 RT673

11 RT703

12 RM191–RM192

19 RT932

2 RT672

31 RT671

AIR PACIFIC (APC)

30 RT502 RT504

AIR PULLMANTUR (PUL)

1 RT523 RT525 RT749

ALL NIPPON AIRWAYS (ANA)

16 RT776

32 RT753–RT755

35 RT777

ASIANA AIRLINES (AAR)

1 RM071 RT131–RT136 RU032

ATLAS AIR (TLS)

33 RT752

AVION AIRCRAFT TRADING H.F. (VNG)

1 RT634

18 RT756

BAHRAIN ROYAL FLIGHT (BHR)

7 RM426

BRITISH AIRWAYS (BAB)

1 RM096–RM097 RM136–RM145 RM261–RM264 RT488–RT499

RU121 RU126–RU132

20 RT480–RT487

29 RT471–RT479

CATHAY PACIFIC AIRWAYS (CAT)

1 RT457–RT469 RT511–RT512 RT514 RT517

RT522 RT529 RT837

14 RT781–RT782

25 RT455

27 RT451–RT454

4 RT518 RT528

5 RT456

6 RT508

CHINA AIRLINES (CHI)

1 RM021–RM024 RT636–RT640

9 RM441–RM443 RM445
 

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BOEING SERVICE BULLETIN 747-28A2281

CORSAIR (COR)

32 RT613–RT614 RT616 RT618–RT619 RT621

DRAGONAIR (DRG)

1 RT519

15 RT510 RT513

4 RT516 RT524

DUBAI AIR WING (DAW)

1 RM167–RM168

10 RT102

EL AL ISRAEL AIRLINES (ELA)

1 RM091 RT527 RU081–RU083

EVA AIR (EVA)

1 RM116–RM117 RT162–RT163 RT165–RT168 RT951–RT955

EVERGREEN INTERNATIONAL A/L (EVR)

1 RT743

EXPORT RESTRICTED AIRPLANES (YWV)

32 RT620

33 RT606

37 RT602

GARUDA INDONESIA (GIA)

1 RU061–RU062

19 RT931

GECAS (GEF)

32 RT412 RT615 RT622

GREAT WALL AIRLINES (GWL)

1 RT520

HIS MAJESTY THE SULTAN'S FLIGHT (BWN)

1 RT440

JAL INTERNATIONAL (JAL)

1 RT861–RT864

2 RT642 RT646–RT650

31 RT641 RT643–RT645

KALITTA AIR (KAC)

28 RT021–RT022

KLM - ROYAL DUTCH AIRLINES (KLM)

1 RM801–RM803 RT006–RT014

29 RT001–RT005
 

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BOEING SERVICE BULLETIN 747-28A2281

KOREAN AIR (KAL)

1 RM011–RM013 RT577–RT588 RT590 RT811–RT814

17 RT572 RT575

20 RT061

23 RT573–RT574 RT576

29 RT571

KUWAIT AIRWAYS (KUW)

1 RT151

LION AIR (MLI)

26 RT503 RT505

LUFTHANSA GERMAN AIRLINES (DLH)

1 RT045–RT047 RT437–RT439 RT441–RT447

21 RT431–RT435

22 RT436

3 RT043–RT044

MALAYSIA AIRLINES (MAS)

1 RM036–RM040 RM366–RM367 RT744 RT746

RT748 RT750 RU016–RU017

MARTINAIR HOLLAND (MTH)

24 RT501 RT506–RT507 RT509

NORTHWEST AIRLINES (NWA)

1 RM241–RM246

20 RT407–RT410

29 RT401–RT406

OMAN ROYAL FLIGHT (RFO)

7 RM010

PHILIPPINE AIRLINES (PAL)

1 RT152 RU051–RU052 RU059–RU060

PRESIDENTIAL FLIGHT (ABD)

1 RM084 RT137

QANTAS (QAN)

1 RF001–RF006 RM331–RM333 RT561–RT568 RT742

RU031

2 RT557–RT560 RT741

31 RT551–RT556

SAUDI ARABIAN AIRLINES (SVA)

1 RU101–RU102

7 RM156–RM157

SAUDI ROYAL FLIGHT (SRF)

7 RM158
 

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BOEING SERVICE BULLETIN 747-28A2281

SINGAPORE AIRLINES (SIA)

1 RM041–RM045 RT521 RT831–RT835

4 RT526 RT530

SONAIR (SON)

1 RM231–RM233

SOUTH AFRICAN AIRWAYS (SAA)

32 RM081 RM083

8 RM147

THAI AIRWAYS INTERNATIONAL (TII)

1 RM026–RM030 RM431 RT694–RT699 RT801–RT803

2 RT693

31 RT691–RT692

TRANSAERO AIRLINES (TRX)

34 RM146 RT783–RT784

UNITED AIR LINES (UAL)

1 RM166 RM169–RM177

32 RT411 RT609–RT612 RT617 RT623–RT630

33 RT605 RT607–RT608

37 RT601 RT603–RT604

UPS (UPS)

1 RT161 RT164

VIRGIN ATLANTIC AIRWAYS (VAA)

1 RM051–RM053 RM351–RM355

32 RT945–RT949

WORLD AIRWAYS, INC. (WLD)

1 RT745 RT747

YANGTZE RIVER EXPRESS (YTH)

18 RT757

IDENTIFICATION BY VARIABLE NUMBER

Variable Group

RF001–RF006 1

RM010 7

RM011–RM013 1

RM021–RM024 1

RM026–RM030 1

RM036–RM045 1

RM051–RM053 1

RM071 1

RM081 32
 

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BOEING SERVICE BULLETIN 747-28A2281

RM082 1

RM083 32

RM084 1

RM091 1

RM096–RM097 1

RM116–RM117 1

RM136–RM145 1

RM146 34

RM147 8

RM156–RM158 7

RM166–RM177 1

RM191–RM192 12

RM231–RM233 1

RM241–RM246 1

RM261–RM264 1

RM331–RM333 1

RM341 1

RM351–RM355 1

RM366–RM367 1

RM401–RM403 1

RM426 7

RM431 1

RM441–RM443 9

RM445 9

RM801–RM803 1

RT001–RT005 29

RT006–RT014 1

RT021–RT022 28

RT043–RT044 3

RT045–RT047 1

RT061 20

RT071–RT073 1

RT101–RT103 10

RT121 1

RT131–RT137 1

RT151–RT152 1

RT161–RT168 1

RT401–RT406 29

RT407–RT410 20

Variable Group
 

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BOEING SERVICE BULLETIN 747-28A2281

RT411–RT412 32

RT431–RT435 21

RT436 22

RT437–RT447 1

RT451–RT454 27

RT455 25

RT456 5

RT457–RT469 1

RT471–RT479 29

RT480–RT487 20

RT488–RT499 1

RT501 24

RT502 30

RT503 26

RT504 30

RT505 26

RT506–RT507 24

RT508 6

RT509 24

RT510 15

RT511–RT512 1

RT513 15

RT514–RT515 1

RT516 4

RT517 1

RT518 4

RT519–RT523 1

RT524 4

RT525 1

RT526 4

RT527 1

RT528 4

RT529 1

RT530 4

RT551–RT556 31

RT557–RT560 2

RT561–RT568 1

RT571 29

RT572 17

Variable Group
 

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BOEING SERVICE BULLETIN 747-28A2281

RT573–RT574 23

RT575 17

RT576 23

RT577–RT588 1

RT590 1

RT591 31

RT601–RT604 37

RT605–RT608 33

RT609–RT630 32

RT633–RT634 1

RT636–RT640 1

RT641 31

RT642 2

RT643–RT645 31

RT646–RT650 2

RT671 31

RT672 2

RT673 1

RT691–RT692 31

RT693 2

RT694–RT699 1

RT701–RT702 13

RT703–RT704 11

RT741 2

RT742–RT750 1

RT751 36

RT752 33

RT753–RT755 32

RT756–RT757 18

RT776 16

RT777 35

RT781–RT782 14

RT783–RT784 34

RT801–RT803 1

RT811–RT814 1

RT831–RT835 1

RT837 1

RT861–RT864 1

RT931–RT932 19

Variable Group
 

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BOEING SERVICE BULLETIN 747-28A2281

2. Spares Affected

None.

B. Concurrent Requirements

Changes given in this service bulletin can not be made unless the changes given in these service 

bulletins are made.

C. Reason

Accomplishment of the changes in this service bulletin will help prevent an ignition source in a fuel 

tank as a result of a horizontal stabilizer override/jettison fuel pump that continues to run after it has 

been commanded off. An ignition source in a fuel tank could result in a fire or an explosion. 

A safety assessment conducted by Boeing indicates that there is a small risk of an ignition source in 

a fuel tank if a horizontal stabilizer override/jettison fuel pump continues to run for an extended time 

after fuel level goes below the pump inlet. Normally the pump is commanded off when a low fuel 

pressure is indicated. If a single failure in the pump control circuitry occurs, a pump can continue to 

run after it is commanded off. When a pump runs after the fuel level goes below the pump inlet, there 

is a small risk that the pump can cause an ignition source in the fuel tank from an overheat condition, 

electrical arcs or frictional sparks. 

RT945–RT949 32

RT951–RT955 1

RU016–RU017 1

RU031–RU032 1

RU051–RU052 1

RU059–RU062 1

RU081–RU083 1

RU101–RU102 1

RU121 1

RU126–RU132 1

Company Service Bulletin Revision Level Description Notes

Boeing 747-28A2262 Original Issue, 

Revision 1, 

Revision 2.

Install automatic shutoff system for the 

Horizontal Stabilizer Tank (HST) fuel pumps.

(a)

(a) This service bulletin is not a concurrent or prior requirement for airplanes RM403, RM441-RM443, 

RM445.

Variable Group
 

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BOEING SERVICE BULLETIN 747-28A2281

This service bulletin gives the instructions to install new relays and wiring in the circuitry for the 

horizontal stabilizer override/jettison fuel pumps. The new relays and wiring for the horizontal 

stabilizer override/jettison fuel pumps remove power from these pumps when the pumps continue to 

run after the pumps have been commanded off. Each set of relays have a new Engine Indication and 

Crew Alerting System (EICAS) status message to annunciate a fault in a pump control relay. For the 

horizontal stabilizer tank, the EICAS status messages are FUEL CMD STAB L and Fuel CMD STAB 

R. These changes help make sure that the risk of an ignition source in a fuel tank is kept to a 

minimum. The changes are identical to the changes to airplanes in production.

This service bulletin is the result of the safety assessments conducted by Boeing under Special 

Federal Aviation Regulation (SFAR) 88, "Fuel Tank System Fault Tolerance Evaluation 

Requirements".

Revision 1 is sent to address the comments received from operators since the original issue of the 

service bulletin and incorporate differences identified during the validation of the service bulletin.

Airplanes RT966-RT967 were deleted from the effectivity. These airplanes are not equipped with 

stabilizer tanks.

As a part of a service bulletin validation program, this change was completed on Airplane RT409 by 

original issue of Service Bulletin 747-28A2281 and before the release of Revision 1 of this service 

bulletin. The change completed on airplane RT409 by Service Bulletin 747-28A2281 is equivalent to 

Revision 1 of this service bulletin. Airplane RT409 has the configuration of a Group 20 airplane.

The data given in Information Notice 747-28A2281 IN 01, IN 02 and IN 03 is included in this revision.

D. Description

Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; 

Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; 

Group 20-22; Group 23, Configuration 2; Group 24-31: Get access to E8 shelf and install new relays. 

Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf 

to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel. 

Rework/install new wiring on P180 panel. Rework wiring from P180 panel to Modularized Avionics 

and Warning Electronics Assembly (MAWEA). Do a functional test. Close access.

Group 9: Get access to E8 shelf and install new relays. Rework/install new wiring on E8 shelf. Get 

access and rework/install new airplane wiring from E8 shelf to disconnect AC1401 and install new 

airplane wiring from disconnect AC1401 to P180 panel. Rework/install new wiring on P180 panel. 

Install new wiring from P180 panel to MAWEA. Do a functional test. Close access.

Group 16; Group 18, Configuration 2; Group 32-37: Get access to E8 shelf and install new relays. 

Rework/install new wiring on E8 shelf. Get access and rework/install new airplane wiring from E8 shelf 

to disconnect AC1401 and rework/install new airplane wiring from disconnect AC1401 to P180 panel 

and add new connector to P180 panel. Rework/install new wiring on P180 panel. Rework wiring from 

P180 panel to MAWEA Card File (P54). Do a functional test. Close access.

Revision 1 - No more work is necessary on airplanes changed as shown in the original issue of this 

service bulletin.

Boeing Service Bulletin 747-28A2280 is related to this service bulletin and has some common access 

procedures.
 

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BOEING SERVICE BULLETIN 747-28A2281

E. Compliance

The Federal Aviation Administration (FAA) will possibly release an Airworthiness Directive related to 

this service bulletin. The Airworthiness Directive will make the compliance tasks and times given in 

this service bulletin mandatory.

Boeing recommends that this service bulletin be incorporated within 5 years after the original issue 

date of this service bulletin.

F. Approval

This service bulletin was examined by the Federal Aviation Administration (FAA). The changes 

specified in this service bulletin comply with the applicable regulations and are FAA approved, as well 

as European Aviation Safety Agency (EASA)/Joint Aviation Authorities (JAA) approved for all EASA/

JAA approved airplanes listed in the service bulletin effectivity. This service bulletin and its approval 

were based on the airplane in its original Boeing delivery configuration or as modified by other 

approved Boeing changes.

If an airplane has a non-Boeing modification or repair that affects a component or system also affected 

by this service bulletin, the operator is responsible for obtaining appropriate regulatory agency 

approval before incorporating this service bulletin.

G. Manpower

The table below shows an estimate of the task-hours necessary to do this service bulletin for each 

airplane. This estimate is for direct labor only, done by an experienced crew. Adjust the estimate with 

operator task-hour data if necessary. The estimate does not include lost time. These are some 

examples of lost time:

— Time to adjust to the workplace

— Time to schedule the work

— Time to examine the work

— Time to cure the materials

— Time to make the parts

— Time to find the tools.

Group 3, Configuration 2; Group 5, Configuration 1; Group 6, Configuration 1; Group 15, Configuration 

1; Group 17, Configuration 1; Group 18, Configuration 1; Group 19, Configuration 2; Group 23, 

Configuration 1: Airplanes, No work is necessary for airplanes in this configuration and no Task-Hours 

are required.

Group 1: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20
 

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Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.20 52.30

Group 18, Configuration 2; Group 32: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 44 2 23.20 11.60

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.20 52.30

Group 2: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Group 1: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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Figure 6 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 33: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 6 2 20.00 10.00

Figure 44 2 23.20 11.60

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 2: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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Group 3, Configuration 1: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 39 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 4; Group 15, Configuration 2; Group 17, Configuration 2: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 5 2 19.80 9.90

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.10 52.25
 

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Group 5, Configuration 2; Group 25: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 6, Configuration 2; Group 24: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 38 2 19.80 9.90

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.10 52.25
 

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Group 7: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 4 2 19.90 9.95

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.20 52.30

Group 8: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 11 2 23.40 11.70

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.40 52.40
 

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Group 34: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 46 2 23.40 11.70

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.40 52.40

Group 9: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 22 1 2.75 2.75

Figure 23 n/a n/a n/a

Figure 24 2 19.90 9.95

Figure 25 2 23.20 11.60

Figure 26 1 1.85 1.85

Figure 27 2 6.40 3.20

Figure 28 2 6.60 3.30

Figure 29 1 2.75 2.75

Figure 30 1 2.85 2.85

Figure 31 2 6.60 3.30

Figure 32 1 2.75 2.75

Figure 33 1 2.85 2.85

Figure 34 1 0.40 0.40

Figure 35 n/a n/a n/a
 

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Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 107.40 55.30

Group 10: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 12 2 23.30 11.65

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 11: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 10 2 23.40 11.70

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Group 9: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.40 52.40

Group 35: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 45 2 23.40 11.70

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.40 52.40

Group 12: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 9 2 23.30 11.65

Figure 13 1 1.85 1.85

Group 11: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 13: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 10 2 23.40 11.70

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.50 52.45

Group 12: 

Task

Number of 

Persons Task-Hours Elapsed Hours
 

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Group 14: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/ n/a

Figure 5 2 19.80 9.90

Figure 11 2 23.40 11.70

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 16: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 7 2 20.00 10.00

Figure 45 2 23.40 11.70

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.50 52.45
 

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Group 19, Configuration 1: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 3 2 19.90 9.95

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.20 52.30

Group 20: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 37 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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Group 21: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 39 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 22: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 39 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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Group 23, Configuration 2: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 38 2 19.80 9.90

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.10 52.25

Group 26: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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Group 27: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 28: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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Group 36: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 40 2 20.00 10.00

Figure 44 2 23.20 11.60

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 15 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 18 2 6.60 3.30

Figure 43 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 29: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 37 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 19 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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Group 30: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 6 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Group 31: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 6 2 20.00 10.00

Figure 8 2 23.20 11.60

Figure 13 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35
 

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H. Weight and Balance Changes

I. Electrical Load Data

1. Direct Current (DC) Loads

2. Alternating Current (AC) Loads

None

3. Type

Group 37: 

Task

Number of 

Persons Task-Hours Elapsed Hours

Open Access 4 13.00 3.25

Figure 1 1 2.75 2.75

Figure 2 n/a n/a n/a

Figure 6 2 20.00 10.00

Figure 44 2 23.20 11.60

Figure 47 1 1.85 1.85

Figure 14 1 0.20 0.20

Figure 41 2 6.60 3.30

Figure 16 1 2.75 2.75

Figure 17 1 2.85 2.85

Figure 42 2 6.60 3.30

Figure 20 1 2.75 2.75

Figure 21 1 2.85 2.85

Figure 36 1 0.40 0.40

Close Access 4 13.00 3.25

Test 2 2.50 1.25

TOTAL FOR EACH AIRPLANE 101.30 52.35

Airplane

Change in Weight 

(Pounds)

Change in Moment 

(Pound-Inches)

Groups 1-8 and 

Groups 10-15, 17, 

19-31

+4.8 lbs +7516.8 lb-in

Group 9 +4.9 lbs +7673.4 lb-in

Groups 16, 18, 32-

37

+4.9 lbs +7673.4 lb-in

Airplanes Amperes Bus

Groups 1-37 0.60 D1P7

0.60 D2P7
 

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Continuous

Intermittent

J. References

1. Existing Data:

a. Engineering Change Memo PRR 85539-8

b. 747-400 Aircraft Maintenance Manual (AMM) 12-11-01, 20-11-16, 24-22-00, 24-29-04; 

25-21-01, 25-22-01, 25-52-01, 25-76-02, 31-61-00, 32-09-02, 34-61-02, 45-10-00, 53-21-02

c. 747 Wiring Diagram 28-21-28, 28-21-31, 28-42-15, 30-41-31

d. Boeing Drawing 012W6100

e. 747 Structural Repair Manual (SRM) Subject 51-40-05

f. Boeing Parts Standards Document D-590

g. Boeing Service Bulletin 747-28-2183

h. Boeing Service Bulletin 747-28-2197

i. Boeing Service Bulletin 747-28-2247

j. Boeing Service Bulletin 747-28-2265

k. Boeing Service Bulletin 747-28-2272

l. Boeing Service Bulletin 747-28-2274

m. Boeing Service Bulletin 747-28-2275

n. Boeing Service Bulletin 747-28A2262

o. Boeing Service Bulletin 747-28A2280

p. Standard Wiring Practices Manual (SWPM) 20-10-11, 20-10-12, 20-10-19, 20-20-00, 

20-30-11, 20-30-12, 20-61-11

2. Data supplied with this Service Bulletin:

None.
 

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3. Installation Drawings Used in the Preparation of this Service Bulletin:

These drawings were used to prepare this service bulletin. These drawings are not necessary 

to make the specified changes, and are not supplied with this service bulletin. These drawings 

may not be applicable to all airplane configurations or operators.

K. Publications Affected

1. Publications

2. Damage Tolerance Based Structural Inspections:

Drawing Number Title

284U4218 Aft Equip Center Assy - E8

288U3080 Modular Wire Bundle Instl, E8, Left Aft Equipment Panel

288U4661 Wire Bundle Installation, Upper Sidewall LH, Sta 2163 thru 2360

288U4641 Wire bundle Installation, Upper Sidewall LH, Sta 1983 thru 2163

288U4645 Wire Bundle Installation, Main deck sidewall LH, Sta 1983 thru 2163

288U4651 Wire Bundle Installation, Main deck floor beams LH, Sta 1983 thru 2163

288U4631 Wire Bundle Installation, Main deck floor beams LH, Sta 1723 thru 1983

288U4611 Wire Bundle Installation, Main deck floor beams LH, Sta 1483 thru 1723

288U4431 Wire Bundle Installation, Pressure deck and main deck FLR BMS LH, 

Sta 1243 thru 1483

288U4411 Wire Bundle Installation, Pressure deck and main deck FLR BMS LH, 

Sta 997 thru 1243

288U4231 Wire Bundle Installation, Main deck floor beams LH, Sta 723 thru 997

288U4211 Wire Bundle Installation, Main deck floor beams LH, Sta 523 thru 723

288U4151 Wire Bundle Installation, Main deck floor beams LH, Sta 403 thru 523 

and aft 400 bulkhead LH

288U4156 Wire Bundle Installation, Main deck floor beams Sta 403 thru 523 LBL 

50 to RBL 60

288U4150 Wire Bundle Installation, Main deck floor beams RH, Sta 403 thru 523 

AFT Sta 400 bulkhead RH

288U4152 Wire Bundle Installation, Main Electronics Equipment Center RH, Sta 

440 thru 460

288U4148 Wire Bundle Installation, Lower Sidewall RH, Sta 403 thru 523

Publication Chapter-Section

747 Maintenance Manual 28-17

747 Fault Isolation Manual 28-31

747 Wiring Diagram Manual 28-21, 28-42, 30-41 

747 System Schematic Manual 28-21, 28-42, 30-41

747 Fault Reporting Manual EICAS Status Messages

747 Illustrated Parts Catalog 28-21
 

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Boeing has evaluated the repairs and/or changes in this service bulletin for effects on Fatigue 

Critical Structure (FCS) and for changes to Damage Tolerance Inspections (DTI) required in the 

Maintenance Program. This service bulletin does not affect FCS, therefore DTIs are not 

necessary.

L. Interchangeability and Intermixability of Parts

Accomplishment of this service bulletin does not affect interchangeability or intermixability of parts.
 

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BLANK PAGE
 

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2. MATERIAL INFORMATION

A. Material - Price and Availability

Boeing can supply the kits/parts shown in Paragraph 2.C., Parts Necessary For Each Airplane, and 

Paragraph 2.D., as shown below. If there is a limit to the quantity (QTY) of available kits/parts, a 

supply sequence is given by Spares. More kits/parts become available as shown in the Reorder Lead 

Time (ROLT). ROLT is calculated from the date Boeing gets the purchase order.

The kits are subject to the terms and conditions of the Boeing standard purchase order 

acknowledgment. After the Unit Price date, new price and ROLT data is applicable. Prices are in 

United States dollars. Terms: Net 30 days.

Reference this service bulletin and submit your purchase order by one of the methods that follow: 

1. Order on-line via ATA Spec 2000 or Boeing Part Page

2. Fax to (206) 662-7145

Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 2; Group

7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, Configuration 2;

Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

 Top Kit Number Name Date QTY

ROLT 

(Weeks) Unit Price thru

015U1808-1 Horizontal Stabilizer 

Tank Jettison Pump 

Uncommanded On.

(a) 50 (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares.

Group 9: 

 Top Kit Number Name Date QTY

ROLT 

(Weeks) Unit Price thru

015U1808-2 Horizontal Stabilizer 

Tank Jettison Pump 

Uncommanded On.

(a) 1 (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares.

Group 16; Group 18, Configuration 2; Group 32-37: 

 Top Kit Number Name Date QTY

ROLT 

(Weeks) Unit Price thru

015U1808-3 Supplemental kit to 

supply connector and 

ID tape. (b)

(a) - (a) (a)

(a) For Top Kit availability and pricing contact Boeing Spares.

(b) Operators who have ordered a 015U1808-1 kit can order the 015U1808-3 kit to complete the 

airplane installation. If an operator has not ordered the 015U1808-1 kit, the operator will need to 

order the 015U1808-1 and 015U1808-3 kits to complete the airplane installation.
 

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3. Spares Customer Support - MC 36-65

Boeing Spares Department

P.O. Box 3707

Seattle, Washington 98124-2207 USA

B. Industry Support Information

Boeing warranty remedies are not available for the configuration changes given in this service bulletin.

C. Parts Necessary For Each Airplane

1. Kits/Parts:

To get the kits/parts shown below, refer to Paragraph 2.A., Material - Price and Availability.
 

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NOTE: One top kit and the items shown in Paragraph 2.C.2., Parts and Materials Supplied by

the Operator, are necessary for each airplane. The Top Kit is divided into Figure kits for

each installation figure shown in the table below.

Figure Kit

Top Kit 1 3 13 14 22 24 26 27 34 36

015U1808-1 1 1 1 1 - - - - - 1

015U1808-2 - - - - 1 1 1 1 1 -

Wire Kit

Top Kit 289U1225-

101

289U1225-

102

289U1225-

103

289U1225-

104

015U1808-1 1 1 1 1

015U1808-2 1 1 1 -

Wire Kit

Top Kit 289U1225-

105

289U1225-

106

015U1808-1 - 1

015U1808-2 1 1

Kit 015U1808-1 - Group 1-2; Group 3, Configuration 1; Group 4-5; Group 5, Configuration 2; 

Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, 

Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 

23, Configuration 2; Group 24-37: 

New Part 

Number

Figure

Name

Existing Part 

Number Notes

1 3 13 14 36

Qty

001-1908-000 4 - - - - TERMINAL BARR

284U4011-45 1 - - - -

RELAY BRACKET 

ASSY

289T9001-21 - 1 - - -

LACING TAPE - 

RED (135C) 100 

FT

289T9001-51 - - - 1 -

LACING TAPE - 

GREEN (135C) 

100 FT

289T9001-91 - - 1 - -

LACING TAPE - 

WHITE (135C) 

100 FT

BAC27EEL19431 1 - - - - MARKER

BAC27EEL29698 1 - - - - VINYL MARKER

BAC27EEL29699 1 - - - - VINYL MARKER

BACC10GE10 - - - - 1 CLAMP, LOOP
 

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BACC10GE5 2 - - - 1 CLAMP, LOOP

BACJ40A20-2 1 - - - -

BONDING 

JUMPER

BACN10YR3CD 8 - - - - NUT

BACS12GU3K10 4 - - - - SCREW

BACS12GU3K8 4 - - - - SCREW

BACS12GU3K9 1 - - - - SCREW, CAP

BACS12HN06-7 1 - - - - BOLT

BACS12HN3-20 - - - - 1 BOLT

BACS12HN3-36 1 - - - - SCREW

BACS12HN3-8 - - - - 1 BOLT

BH315 2 - - - -

RELAY,25A,W/

AUX

NAS1149D0316H 10 - - - - WASHER

NAS1149D0332J 10 - - - 2 WASHER

NAS42DD6-64FC 2 - - - 1

SPACERS FOR 

RIVETS

Kit 015U1808-2 - Group 9: 

New Part 

Number

Figure

Name

Existing Part 

Number Notes

22 24 26 27 34

Qty

001-1908-000 4 - - - - TERMINAL BARR

284U4011-45 1 - - - -

RELAY BRACKET 

ASSY

289T9001-21 - 1 - - -

LACING TAPE - 

RED (135C) 100 

FT

289T9001-51 - - - 1 -

LACING TAPE - 

GREEN (135C) 

100 FT

289T9001-91 - - 1 - -

LACING TAPE - 

WHITE (135C) 

100 FT

BAC27EEL19431 1 - - - - MARKER

BAC27EEL29698 1 - - - - VINYL MARKER

Kit 015U1808-1 - Group 1-2; Group 3, Configuration 1; Group 4-5; Group 5, Configuration 2; 

Group 6, Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, 

Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 

23, Configuration 2; Group 24-37: 

New Part 

Number

Figure

Name

Existing Part 

Number Notes

1 3 13 14 36

Qty
 

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BAC27EEL29699 1 - - - - VINYL MARKER

BACC10GE10 - - - - 1 CLAMP, LOOP

BACC10GE5 2 - - - 1 CLAMP, LOOP

BACJ40A20-2 1 - - - -

BONDING 

JUMPER

BACN10YR3CD 8 - - - - NUT

BACS12GU3K10 4 - - - - SCREW

BACS12GU3K8 4 - - - - SCREW

BACS12GU3K9 1 - - - - SCREW, CAP

BACS12HN06-7 1 - - - - BOLT

BACS12HN3-20 - - - - 1 BOLT

BACS12HN3-36 1 - - - - SCREW

BACS12HN3-8 - - - - 1 BOLT

BH315 2 - - - -

RELAY,25A,W/

AUX

NAS1149D0316H 10 - - - - WASHER

NAS1149D0332J 10 - - - 2 WASHER

NAS42DD6-64FC 2 - - - 1

SPACERS FOR 

RIVETS

Kit 289U1225-101 - Group 1-2; Group 3, Configuration 1; Group 4-5; 

Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group 

15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, 

Configuration 2; Group 24-37: 

New Part Number

-101

Qty Name Notes

289U1225-101W 1 WIRE - RAW MATERIAL

BACC47CN1S 3 CONTACT, PIN

BACC47CP1S 3 CONTACT

M23053/5-107-4 3

INSULATION SLEEVING, 

HEAT SHRINKABLE, 

POLYOLEFIN, FLEXIBLE, 

X-LINKED

Kit 015U1808-2 - Group 9: 

New Part 

Number

Figure

Name

Existing Part 

Number Notes

22 24 26 27 34

Qty
 

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Kit 289U1225-102 - Group 1-2; Group 3, Configuration 1; Group 4; 

Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group 

15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, 

Configuration 2; Group 24-37: 

New Part Number

-102

Qty Name Notes

289U1225-102W 1 WIRE - RAW MATERIAL

BACC47CN1S 3 CONTACT, PIN

BACC47CP1S 3 CONTACT

M23053/5-107-4 3

INSULATION SLEEVING, 

HEAT SHRINKABLE, 

POLYOLEFIN, FLEXIBLE, 

X-LINKED

Kit 289U1225-103 - Group 1-2; Group 3, Configuration 1; Group 4-5; 

Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group 

15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, 

Configuration 2; Group 24-37: 

New Part Number

-103

Qty Name Notes

289U1225-103W 1 WIRE - RAW MATERIAL

BACC47CN1S 3 CONTACT, PIN

BACC47CP1S 3 CONTACT

Kit 289U1225-104 - Group 1-2; Group 3, Configuration 1; Group 4; 

Group 5, Configuration 2; Group 6, Configuration 2; Group 7-8, 10-14; 

Group 15, Configuration 2; Group 16; Group 17, Configuration 2; 

Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; 

Group 23, Configuration 2; Group 24-37: 

New Part Number

-104

Qty Name Notes

BACC47EG2 3 CONTACT, SOCKET

Kit 289U1225-105 - Group 9: 

New Part Number

-105

Qty Name Notes

289U1225-105W 1 WIRE - RAW MATERIAL

BACC47EG2 3 CONTACT, SOCKET
 

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Kit 289U1225-106 - Group 1-2; Group 3, Configuration 1; Group 4; 

Group 5, Configuration 2; Group 6, Configuration 2; Group 7-14; Group 

15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, 

Configuration 2; Group 24-37: 

New Part Number

-106

Qty Name Notes

289U1225-106W 1 WIRE - RAW MATERIAL

BACC47CN1S 3 CONTACT, PIN

BACC47CP1S 3 CONTACT

BACC47CP3T 7 CONTACT

BACT12AC12 7 TERMINAL, LUG

BACT12AC2 21 TERMINAL, LUG

BACT12E10 13 TERMINAL, LUG

D436-38 3 SPLICE

Kit 015U1808-3 - Group 16; Group 18, Configuration 2; Group 32-37: 

New Part 

Number

-3

Name

Existing Part 

Qty Number Notes

289U1225-10701 1

ID TAPE - 

CONNECTOR

289U1225-10801 1

ID TAPE - 

CONNECTOR

BACC45FN16-

24S6 1

CONNECTOR, 

ELECTRICAL, 

RECEPTACLE, 

FLANGE MOUNT, 

BAYONET 

COUPLING

BACC45FT16-

24P6 1

CONNECTOR, 

ELECTRICAL, 

PLUG, 

STRAIGHT, 

BAYONET 

COUPLING

BACC47CN1S 2 CONTACT, PIN

BACC47CP1S 2

CONTACT, 

SOCKET

BACN10JC04CM 3 NUT

BACS12HN04U6 3 SCREW

NAS1149DN332J 3 WASHER, PLAIN
 

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2. Parts and Materials Supplied by the Operator:

3. Parts Modified and Reidentified:

None.

4. Parts Removed and Not Replaced:

None.

D. Parts Necessary to Change Spares

None.

E. Special Tooling - Price and Availability

None.

F. Special Tooling Necessary to do this Service Bulletin

No special tools or equipment are necessary to do the change in this service bulletin. But, 

maintenance and overhaul tools in the manuals given in Paragraph 1.J., References, can be 

necessary. Examine operator tool supply to make sure all necessary tools are available.

Part Number / 

Specification QTY Name Notes

BMS 10-11, TYPE 

1

1 pt PRIMER (a)

BMS 5-95 1 pt SEALANT (a)

NAS1149D616H 

or equivalent

1 Washer (b)

BACN10YR06CD 

or equivalent

1 Nut (b)

(a) See the Qualified Products List at the end of the Boeing Material 

Specification (BMS) for supplier data.

(b) If relay mounting bracket hole requires relocation (see Figure 1, Circle 

Note 3) these parts or equivalent may be required.
 

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3. ACCOMPLISHMENT INSTRUCTIONS

A. GENERAL INFORMATION

CAUTION: KEEP THE WORK AREA, WIRES AND ELECTRICAL BUNDLES CLEAN OF METAL

PARTICLES OR CONTAMINATION WHEN YOU USE TOOLS. UNWANTED

MATERIAL, METAL PARTICLES OR CONTAMINATION CAUGHT IN WIRE BUNDLES

CAN CAUSE DAMAGE TO THE BUNDLES. DAMAGED WIRE BUNDLES CAN CAUSE

SPARKS OR OTHER ELECTRICAL DAMAGE.

NOTE:

1. The instructions identified in Paragraph 3.B. Work Instructions and the Figures(s) give 

the recommended sequence of steps. The sequence of steps to do this service bulletin 

can be changed.

2. Manual titles are referred to by acronyms. Refer to Paragraph 1.J., References, for 

definition of the acronyms.

3. Obey all of the warnings and cautions given in the specified manual sections.

4. Unless shown differently, these dimensions and tolerances are used:

— Linear dimensions are in inches.

— Tolerance on linear dimensions, other than rivet and bolt edge margins, is plus or 

minus 0.03 inch.

— Tolerance on rivet and bolt edge margin is plus or minus 0.05 inch.

— Hole dimensions for standard solid rivets are in 747 SRM, Chapter 51.

— Torque limits to tighten nuts and bolts are in 747 SRM, Chapter 51.

5. Use the approved fastener and process material substitutions in accordance with 747 

SRM, Chapter 51.

6. Refer to the SWPM 20-10-11 and SWPM 20-10-12 for the wire installation procedures, 

and SWPM 20-10-19 for wire separation requirements, as accepted procedures.

7. The necessary conditions for selection of a clamp and clamp size are included in SWPM 

20-10-12. If the clamp size for the wire harness supports specified in this service bulletin 

does not make a correct fit on the wire bundle, refer to SWPM 20-10-12 as an accepted 

procedure to select the correct clamp.

8. If the length of any fastener specified in this service bulletin does not meet the 

installation standards in 747 SRM, Chapter 51, then a fastener of the same specification, 

or an approved substitute, with a length which meets the installation standards in 747 

SRM, Chapter 51 may be used.

9. These work instructions refer to procedures included on other Boeing documents. 

When the words "refer to" are used and the operator has an accepted alternative 

procedure, the accepted alternative procedure can be used. When the words "as given 

in" are included in the instruction, the procedure in the Boeing document must be used.

B. WORK INSTRUCTIONS

Group 3, Configuration 2; Group 5, Configuration 1; Group 6, Configuration 1; Group 15, 
 

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Configuration 1; Group 17, Configuration 1; Group 18, Configuration 1; Group 19, 

Configuration 2; Group 23, Configuration 1: Airplanes

1. Airplanes - No work is necessary for airplanes in this configuration. The airplanes in this 

configuration do not have active Horizontal Stabilizer Tanks.

Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, 

Configuration 2; Group 18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 

23, Configuration 2; Group 24-37: Airplanes

1. Gain access to the rework area as follows:

a. If the airplane has a crew rest located over door 5 remove the sidewall partitions as 

necessary for access to the E-8 shelf and wire bundle routing, refer to 747-400 AMM 

25-76-02.

b. If the airplane has no crew rest located over door 5 remove the ceiling and lower side wall 

linings (station 2320 to 2300) as necessary for access to E-8 shelf and wire bundle routing, 

refer to 747-400 AMM 25-21-01 and 747-400 AMM 25-22-01 as accepted procedures.

c. Remove the ceiling panels in the passenger compartment (station 2310 to station 2100 and 

some airplanes to station 1980) as necessary for access to the outer portion of the sidewall 

where required for routing of ships wire bundles, refer to 747-400 AMM 25-22-01 as an 

accepted procedure.

d. Remove the ceiling panels in the rear cargo compartment (station 2100 or station 1980 to 

station 1480 as necessary for access to the cargo compartment ceiling where required for 

routing of ships wire bundles, refer to 747-400 AMM 25-52-01 as an accepted procedure.

e. Remove the floor panels on the main deck (station 1480 to station 980) as necessary for 

access to the wire bundles that route between the forward cargo compartment and the aft 

cargo compartment, refer to 747-400 AMM 53-21-02 as an accepted procedure. Some 

airplanes may have the wire bundle routed in a conduit and removal of the floor panels may 

not be required.

f. Remove cargo ceiling linings in the forward cargo compartment (station 980 to station 400) 

as necessary to access the wire bundles that route in the forward cargo compartment ceiling 

and to the main equipment bay, refer to 747-400 AMM 25-52-01 as an accepted procedure.

NOTE: Operators should check their applicable wiring configurations to determine how much

access will be required.

2. Remove electrical power from the airplane, refer to 747-400 AMM 24-22-00 as an accepted 

procedure.

3. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Install new relays on the E-8 shelf as given in Figure 1.
 

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4. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Make wiring changes using the routing shown, for wire bundles W4488 and W4588, as given in 

Figure 2 and for wire bundle routing for wire bundle W3851, as given in Figure 36.

5. Group 1, 8, 10-12; Group 18, Configuration 2; Group 19, Configuration 1; Group 32, 34-35: 

Make wiring changes to wire bundle W4488 as given in Figure 3 and Figure 2

6. Group 7: 

Make wiring changes to wire bundle W4488 as given in Figure 4 and Figure 2.

7. Group 4, 14; Group 15, Configuration 2; Group 17, Configuration 2: 

Make wiring changes to wire bundle W4488 as given in Figure 5 and Figure 2.

8. Group 2, 30-31, 33, 37: 

Make wiring changes to wire bundle W4488 as given in Figure 6 and Figure 2.

9. Group 16: 

Make wiring changes to wire bundle W4488 as given in Figure 7 and Figure 2.

10. Group 20, 29: 

Make wiring changes to wire bundle W4488 as given in Figure 37 and Figure 2

11. Group 6, Configuration 2; Group 23, Configuration 2; Group 24: 

Make wiring changes to wire bundle W4488 as given in Figure 38 and Figure 2.

12. Group 3, Configuration 1; Group 21-22: 

Make wiring changes to wire bundle W4488 as given in Figure 39 and Figure 2.

13. Group 5, Configuration 2; Group 13, 25-28, 36: 

Make wiring changes to wire bundle W4488 as given in Figure 40 and Figure 2.

14. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; 

Group 20-22; Group 23, Configuration 2; Group 24-31: 

Make wiring changes to wire bundle W4588 as given in Figure 8 and Figure 2.

15. Group 18, Configuration 2; Group 32-33, 36-37: 

Make wiring changes to wire bundle W4588 as given in Figure 44 and Figure 2.
 

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16. Group 12: 

Make wiring changes to wire bundle W4588 as given in Figure 9 and Figure 2.

17. Group 11, 13: 

Make wiring changes to wire bundle W4588 as given in Figure 10 and Figure 2.

18. Group 16, 35: 

Make wiring changes to wire bundle W4588 as given in Figure 45 and Figure 2.

19. Group 8, 14: 

Make wiring changes to wire bundle W4588 as given in Figure 11 and Figure 2.

20. Group 34: 

Make wiring changes to wire bundle W4588 as given in Figure 46 and Figure 2.

21. Group 10: 

Make wiring changes to wire bundle W4588 as given in Figure 12 and Figure 2.

22. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, 

Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: 

Make wiring changes to wire bundle W3845 as given in Figure 13.

23. Group 16; Group 18, Configuration 2; Group 32-37: 

Make wiring changes to wire bundle W3845 as given in Figure 47.

24. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Make wiring changes to wire bundle W4758 as given in Figure 14. See Figure 2 and 35 for 

MAWEA card file location and wire routing information.

25. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 15 and Figure 36.

26. Group 19, Configuration 1; Group 21, 26-27, 29-31, 37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 41 and Figure 36.
 

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27. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 16 and Figure 36.

28. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 17 and Figure 36.

29. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20, 22; Group 23, Configuration 2; Group 

24-25, 28, 32-36: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 18 and Figure 36.

30. Group 21, 26-27, 29-31, 37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 42 and Figure 36.

31. Group 3, Configuration 1; Group 7, 20-22, 29: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 19 and Figure 36.

32. Group 5, Configuration 2; Group 6, Configuration 2; Group 13; Group 23, Configuration 2; Group 

24-28, 36: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 43 and Figure 36.

33. Group 1-2, 4, 8, 10-12, 14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; 

Group 18, Configuration 2; Group 19, Configuration 1; Group 30-35, 37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 20 and Figure 36.

34. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Make wiring changes to wire bundle W3851 and route wiring as given in Figure 21 and Figure 36.

35. Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, Configuration 

2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 

18, Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 

24-37: 

Do the functional test.
 

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a. Prepare for the test.

(1) Obey these precautions at all times during these tests:

(a) To operate any of the fuel pumps, you must be in the flight compartment to 

continuously monitor the fuel quantity and low pressure indication in the applicable 

tank.

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE

INDICATION COMES ON AND STAYS ON. FUEL VAPORS IN THE

TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.

(b) Immediately set the applicable fuel pump switch to the OFF position if the low 

pressure indication light comes on and stays on.

(2) Make sure that power is supplied to the airplane. Refer to 747-400 AMM 24-22-00 as 

an accepted procedure.

(3) Make sure the airplane is in ground mode. Refer to 747-400 AMM 32-09-02 as an 

accepted procedure.

(4) Make sure that the Computer Display Unit (CDU) is installed. Refer to 747-400 AMM 

34-61-02 as an accepted procedure. 

(5) Make sure that the fuel jettison system is serviceable.

(6) Make sure that the Integrated Display System (IDS) is serviceable. Refer to 747-400 

AMM 31-61-00 as an accepted procedure.

(7) Make sure that the Central Maintenance Computer (CMC) is serviceable. Refer to 

747-400 AMM 45-10-00 as an accepted procedure.

(8) Make sure that the Horizontal Stabilizer Tanks (HST) have the fuel quantities as 

follows:

(a) Make sure there is 2,000 pounds (907 kilograms) or more of fuel in the HST.

NOTE: This fuel will prevent dry operation of the jettison pumps.

(b) If the quantity of fuel is not sufficient, refer to 747-400 AMM 12-11-01 as an 

accepted procedure.

(9) Open the refueling station door.

b. Do this test of the automatic pump shutoff for the Left HST Fuel Pump:

(1) Make sure the following circuit breaker on the P85 panel is closed:

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left
 

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(2) Make sure the following circuit breakers on the P414 panel are closed:

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on P42. 

(5) Set the S14 L HSTAB Pump switch on the M154 panel to ON.

(6) Verify L HSTAB fuel pump is running.

(7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03141, start timing with a 

stopwatch.

(9) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left 

(located on E8 shelf) are energized for more than 20 seconds.

(10) Set the S14 L STAB pump switch on the M154 panel to OFF.

(11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on P42.

(12) Open the following circuit breakers on the P414 panel:

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7393 Rly-Jtsn Ovrd-Left on the P414.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont
 

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(15) Close the following circuit breaker on the P85 panel:

(16) Close the following circuit breakers on the P414 panel:

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(19) Set the S14 L HSTAB Pump switch on the M154 panel to ON.

(20) Verify L HSTAB fuel pump is running.

(21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03141, start timing with a 

stopwatch.

(23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and 

R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized.

(24) Verify Left Pump Low Pressure light ILLUMINATED. 

(25) Set the S14 L STAB Pump switch on the M154 panel to OFF.

(26) Verify Left Low Pressure light EXTINGUISHES.

(27) Set the S14 L HSTAB Pump switch on the M154 panel to ON.

(28) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left 

Relay (located on E8 shelf) are energized.

(29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and 

R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized.

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left
 

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(30) Set the S14 L STAB Pump switch on the M154 panel to OFF.

(31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(34) Reconnect pin B1 to relay R7393 Rly-Jtsn Ovrd-Left on the P414 panel.

(35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(39) Set the S14 L STAB Pump switch on the M154 panel to ON.

(40) At the same time the S14 L STAB Pump switch on the M154 panel is CLOSED, start 

timing with a stopwatch.

(41) Verify L HSTAB fuel pump is running more than 20 seconds.

(42) Set the S14 L STAB Pump switch on the M154 panel to OFF.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont
 

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(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

c. Do this test of the Uncommanded On for the LEFT HST FUEL PUMP:

WARNING: VERIFY S14 L STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF

POSITION BEFORE DOING THE UNCOMMANDED ON TEST.

(1) Ground Pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. 

(2) Wait for a minimum of 60 seconds and check the Engine Indication and Crew Alerting 

System (EICAS) Status Message, the following message should be displayed on the 

EICAS Status "FUEL CMD STAB L".

(3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and 

B2, pins C1 and C2 and pins to ground of relay R7401 and relay R1365 on the E8 shelf. 

Verify that the resistance value shows an OPEN circuit.

(4) Remove the ground jumper at pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left 

relay.

d. Do this test of the automatic pump shutoff for the Right STAB Fuel Pump:

(1) Make sure the following circuit breaker on the P85 panel is closed:

C/B Number Location Name

C10125 H25 HSTAB-L Refuel 

&Xfer Cont

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right
 

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(2) Make sure the following circuit breakers on the P414 panel are closed:

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. 

(5) Set the S15 R STAB Pump switch on the M154 panel to ON.

(6) Verify R HSTAB fuel pump is running.

(7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03142, start timing with a 

stopwatch.

(9) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont 

Right (located on E8 shelf) are energized for more than 20 seconds.

(10) Set the S15 R STAB pump switch on the M154 panel to OFF.

(11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(12) Open the following circuit breakers on the P414 panel:

(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7394 Rly-Jtsn Ovrd-Right on the P415.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont
 

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(15) Close the following circuit breaker on the P85 panel:

(16) Close the following circuit breakers on the P414 panel:

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(19) Set the S15 R STAB Pump switch on the M154 panel to ON.

(20) Verify R HSTAB fuel pump is running.

(21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03142, start timing with a 

stopwatch.

(23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and 

R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized.

(24) Verify Right Pump Low Pressure light ILLUMINATED. 

(25) Set the S15 R STAB Pump switch on the M154 panel to OFF.

(26) Verify Right Low Pressure light EXTINGUISHES.

(27) Set the S15 R STAB Pump switch on the M154 panel to ON.

(28) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont 

Right Relay (located on E8 shelf) are energized.

(29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and 

R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized.

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right
 

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(30) Set the S15 R STAB Pump switch on the M154 panel to OFF.

(31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(34) Reconnect pin B1 to relay R7394 Rly-Jtsn Ovrd-Right on the P415 panel.

(35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(39) Set the S15 R STAB Pump switch on the M154 panel to ON.

(40) At the same time the S15 R STAB Pump switch on the M154 Panel is CLOSED, start 

timing with a stopwatch.

(41) Verify R HSTAB fuel pump is running more than 20 seconds.

(42) Set the S15 R STAB Pump switch on the M154 panel to OFF.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont
 

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(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

e. Do this test of the Uncommanded On for the RIGHT HST FUEL PUMP:

WARNING: VERIFY S15 R STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF

POSITION BEFORE DOING THE UNCOMMANDED ON TEST.

(1) Ground Pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. 

(2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following 

message should be displayed on the EICAS Status "FUEL CMD STAB R".

(3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and 

B2, pins C1 and C2 and pins to ground of relay R7402 and relay R1366 on the E8 shelf. 

Verify that the resistance value shows an OPEN circuit.

(4) Remove the ground jumper at pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right 

relay.

(5) Clear the following EICAS Status Messages using the CMC:

— "FUEL CMD STAB L"

— "FUEL CMD STAB R"

(6) After 60 seconds, verfiy the following messages are NOT displayed on the EICAS 

Status:

— "FUEL CMD STAB L"

— "FUEL CMD STAB R"

36. CLOSE Fueling Station Door.

37. Close access to the main equipment center.

38. Put the airplane back to a serviceable condition.

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right
 

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Group 9: Airplanes

1. Gain access to the rework area as follows:

NOTE: Operators should check their applicable wiring configurations to determine how much

access will be required.

a. If the airplane has a crew rest located over door 5 remove the sidewall partitions as 

necessary for access to the E-8 shelf and wire bundle routing, refer to 747-400 AMM 

25-76-02 as an accepted procedure.

b. If the airplane has no crew rest located over door 5 remove the ceiling and lower side wall 

linings (station 2320 to 2300) as necessary for access to E-8 shelf and wire bundle routing, 

refer to 747-400 AMM 25-21-01 and 747-400 AMM 25-22-01 as accepted procedures.

c. Remove the ceiling panels in the passenger compartment (station 2310 to station 2100 and 

some airplanes to station 1980) as necessary for access to the outer portion of the sidewall 

where required for routing of ships wire bundles, refer to 747-400 AMM 25-22-01 as an 

accepted procedure.

d. Remove the ceiling panels in the rear cargo compartment (station 2100 or station 1980 to 

station 1480 as necessary for access to the cargo compartment ceiling where required for 

routing of ships wire bundles, refer to 747-400 AMM 25-52-01 as an accepted procedure.

e. Remove the floor panels on the main deck (station 1480 to station 980) as necessary for 

access to the wire bundles that route between the forward cargo compartment and the aft 

cargo compartment, refer to 747-400 AMM 53-21-02 as an accepted procedure. Some 

airplanes may have the wire bundle routed in a conduit and removal of the floor panels may 

not be required.

f. Remove cargo ceiling linings in the forward cargo compartment (station 980 to station 400) 

as necessary to access the wire bundles that route in the forward cargo compartment ceiling 

and to the main equipment bay, refer to 747-400 AMM 25-52-01 as an accepted procedure.

2. Remove electrical power from the airplane, refer to 747-400 AMM 24-22-00 as an accepted 

procedure.

3. Install new relays on the E-8 shelf as given in Figure 22.

4. Make wiring changes using the routing shown, refer to Figure 23 for wire bundles W4488 and 

W4588 and for wire bundle W3851, refer to Figure 34.

5. Make wiring changes to wire bundle W4488 as given in Figure 24 and Figure 23.

6. Make wiring changes to wire bundle W4588 as given in Figure 25 and Figure 23.

7. Make wiring changes to wire bundle W3845 as given in Figure 26.

8. Make wiring changes to wire bundle W4758 and route wiring as given in Figure 27 and Figure 35.

9. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 28 and Figure 34.

10. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 29 and Figure 34.
 

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11. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 30 and Figure 34.

12. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 31 and Figure 34.

13. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 32 and Figure 34.

14. Make wiring changes to wire bundle W3851 and route wiring as given in Figure 33 and Figure 34.

15. Group 9: Do the functional test.

a. Prepare for the test.

(1) Obey these precautions at all times during these tests:

(a) To operate any of the fuel pumps, you must be in the flight compartment to 

continuously monitor the fuel quantity and low pressure indication in the applicable 

tank.

WARNING: DO NOT OPERATE A FUEL PUMP IF THE LOW PRESSURE

INDICATION COMES ON AND STAYS ON. FUEL VAPORS IN THE

TANK MAY IGNITE AND CAUSE A FIRE OR EXPLOSION.

(b) Immediately set the applicable fuel pump switch to the OFF position if the low 

pressure indication light comes on and stays on.

(2) Make sure that power is supplied to the airplane. Refer to 747-400 AMM 24-22-00 as 

an accepted procedure.

(3) Make sure the airplane is in ground mode. Refer to 747-400 AMM 32-09-02 as an 

accepted procedure.

(4) Make sure that the CDU is installed. Refer to 747-400 AMM 34-61-02 as an accepted 

procedure. 

(5) Make sure that the fuel jettison system is serviceable.

(6) Make sure that the Integrated Display System (IDS) is serviceable. Refer to 747-400 

AMM 31-61-00 as an accepted procedure.

(7) Make sure that the Central Maintenance Computer (CMC) is serviceable. Refer to 

747-400 AMM 45-10-00 as an accepted procedure.

(8) Make sure that the Horizontal Stabilizer Tanks (HST) have the fuel quantities as 

follows:

(a) Make sure there is 2,000 pounds (907 kilograms) or more of fuel in the HST.

NOTE: This fuel will prevent dry operation of the jettison pumps.

(b) If the quantity of fuel is not sufficient, refer to 747-400 AMM 12-11-01 as an 

accepted procedure.

(9) Open the refueling station door.
 

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b. Do this test of the automatic pump shutoff for the Left HST Fuel Pump:

(1) Make sure the following circuit breaker on the P85 panel is closed:

(2) Make sure the following circuit breakers on the P414 panel are closed:

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" P42. 

(5) Set the S14 L STAB Pump switch on the M154 panel to ON.

(6) Verify L HSTAB fuel pump is running.

(7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03141, start timing with a 

stopwatch.

(9) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left 

(located on E8 shelf) are energized for more than 20 seconds.

(10) Set the S14 L STAB pump switch on the M154 panel to OFF.

(11) Close S1879 Switch Horiz-Stab ISLN Con VLV P42.

(12) Open the following circuit breakers on the P414 panel:

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr
 

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(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7393 Rly-Jtsn Ovrd-Left on the P414.

(15) Close the following circuit breaker on the P85 panel:

(16) Close the following circuit breakers on the P414 panel:

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(19) Set the S14 L STAB Pump switch on the M154 panel to ON.

(20) Verify L HSTAB fuel pump is running.

(21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03141, start timing with a 

stopwatch.

(23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and 

R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized.

(24) Verify Left Pump Low Pressure light ILLUMINATED. 

(25) Set the S14 L STAB Pump switch on the M154 panel to OFF.

(26) Verify Left Low Pressure light EXTINGUISHES.

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left
 

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(27) Set the S14 L STAB Pump switch on the M154 panel to ON.

(28) Use an ohmmeter to verify, the relays R7401 and R1365 RLY-HSTAB Pump Cont Left 

Relay (located on E8 shelf) are energized.

(29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7401 and 

R1365 RLY-HSTAB Pump Cont Left Relay (located on E8 shelf) are de-energized.

(30) Set the S14 L STAB Pump switch on the M154 panel to OFF.

(31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(34) Reconnect pin B1 to relay R7393 Rly-Jtsn Ovrd-Left on the P414 panel.

(35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(39) Set the S14 L STAB Pump switch on the M154 panel to ON.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont
 

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(40) At the same time the S14 L STAB Pump switch on the M154 panel is CLOSED, start 

timing with a stopwatch.

(41) Verify L HSTAB fuel pump is running more than 20 seconds.

(42) Set the S14 L STAB Pump switch on the M154 panel to OFF.

(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch Horiz-Stab ISLN Con VLV on the P42 panel.

c. Do this test of the Uncommanded On for the LEFT HST FUEL PUMP:

WARNING: VERIFY S14 L STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF

POSITION BEFORE DOING THE UNCOMMANDED ON TEST.

(1) Ground Pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left relay. 

(2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following 

message should be displayed on the EICAS Status "FUEL CMD STAB L".

(3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and 

B2, pins C1 and C2 and pins to ground of relay R7401 and relay R1365 on the E8 shelf. 

Verify that the resistance value shows an OPEN circuit.

(4) Remove the ground jumper at pin 11 on relay R7401 RLY-HSTAB Pump Cont - Left 

relay.

d. Do this test of the automatic pump shutoff for the Right STAB Fuel Pump:

C/B Number Location Name

C10125 H25 HSTAB-L Refuel & 

Xfer Cont

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C03141 Horiz Stab Xfer/Jett 

Pump Left
 

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(1) Make sure the following circuit breaker on the P85 panel is closed:

(2) Make sure the following circuit breakers on the P414 panel are closed:

(3) Make sure the following circuit breaker on the P7 panel is closed:

(4) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel. 

(5) Set the S15 R STAB Pump switch on the M154 panel to ON.

(6) Verify R HSTAB fuel pump is running.

(7) Open the following circuit breaker on the P85 panel:

(8) At the same time as you OPEN the circuit breaker C03142, start timing with a 

stopwatch.

(9) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont 

Right (located on E8 shelf) are energized for more than 20 seconds.

(10) Set the S15 R STAB pump switch on the M154 panel to OFF.

(11) Close S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(12) Open the following circuit breakers on the P414 panel:

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr
 

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(13) Open the following circuit breaker on the P7 panel:

(14) Disconnect pin B1 from relay R7394 Rly-Jtsn Ovrd-Right on the P415.

(15) Close the following circuit breaker on the P85 panel:

(16) Close the following circuit breakers on the P414 panel:

(17) Close the following circuit breaker on the P7 panel:

(18) Open S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(19) Set the S15 R STAB Pump switch on the M154 panel to ON.

(20) Verify R HSTAB fuel pump is running.

(21) Open the following circuit breaker on the P85 panel:

(22) At the same time as you OPEN the circuit breaker C03142, start timing with a 

stopwatch.

(23) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and 

R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized.

(24) Verify Right Pump Low Pressure light ILLUMINATED. 

(25) Set the S15 R STAB Pump switch on the M154 panel to OFF.

(26) Verify Right Low Pressure light EXTINGUISHES.

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right
 

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(27) Set the S15 R STAB Pump switch on the M154 panel to ON.

(28) Use an ohmmeter to verify, the relays R7402 and R1366 RLY-HSTAB Pump Cont 

Right Relay (located on E8 shelf) are energized.

(29) Use an ohmmeter to verify, that after approximately 14 seconds, the relays R7402 and 

R1366 RLY-HSTAB Pump Cont Right Relay (located on E8 shelf) are de-energized.

(30) Set the S15 R STAB Pump switch on the M154 panel to OFF.

(31) Open the following circuit breakers on the P414 panel:

(32) Open the following circuit breaker on the P7 panel:

(33) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(34) Reconnect pin B1 to relay R7394 Rly-Jtsn Ovrd-Right on the P415 panel.

(35) CLOSE the following circuit breaker on the P85 panel:

(36) CLOSE the following circuit breakers on the P414 panel:

(37) CLOSE the following circuit breaker on the P7 panel:

(38) OPEN S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

(39) Set the S15 R STAB Pump switch on the M154 panel to ON.

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont
 

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(40) At the same time the S15 R STAB Pump switch on the M154 panel is CLOSED, start 

timing with a stopwatch.

(41) Verify R HSTAB fuel pump is running more than 20 seconds.

(42) Set the S15 R STAB Pump switch on the M154 panel to OFF.

(43) OPEN the following circuit breaker on the P7 panel:

(44) OPEN the following circuit breakers on the P414 panel:

(45) OPEN the following circuit breaker on the P85 panel:

(46) CLOSE S1879 Switch "Horiz-Stab ISLN Con VLV" on the P42 panel.

e. Do this test of the Uncommanded On for the RIGHT HST FUEL PUMP:

WARNING: VERIFY S15 R STAB PUMP SWITCH ON THE P154 PANEL IS IN THE OFF

POSITION BEFORE DOING THE UNCOMMANDED ON TEST.

(1) Ground Pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right relay. 

(2) Wait for a minimum of 60 seconds and check the EICAS Status Message, the following 

message should be displayed on the EICAS Status "FUEL CMD STAB R".

(3) Use an ohmmeter to measure the resistance between the pins A1 and A2, pins B1 and 

B2, pins C1 and C2 and pins to ground of relay R7402 and relay R1366 on the E8 shelf. 

Verify that the resistance value shows an OPEN circuit.

(4) Remove the ground jumper at pin 11 on relay R7402 RLY-HSTAB Pump Cont - Right 

relay.

(5) Clear the following EICAS Status Messages using the CMC:

— "FUEL CMD STAB L"

— "FUEL CMD STAB R"

(6) After 60 seconds, verfiy the following messages are NOT displayed on the EICAS 

Status:

— "FUEL CMD STAB L"

C/B Number Location Name

C10126 H26 HSTAB-R Refuel & 

Xfer Cont

C/B Number Location Name

C00090 F17 Fueling Valve

C01142 F22 Fueling Pwr

C/B Number Location Name

C03142 Horiz Stab Xfer/Jett 

Pump Right
 

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— "FUEL CMD STAB R"

16. CLOSE Fueling Station Door.

17. CLOSE access to the main equipment center.

18. Put the airplane back to a serviceable condition.
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 1: INSTALL RELAYS ON E-8 SHELF

UP

FWD

INBD

AFT E/E

EQUIPMENT CENTER

ENTRY

DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT

CENTER - E8

STA

2302.94

STA

2302.94

FOR ALTERNATE

CONFIGURATION

INBD FWD

1

2

19

SEE A 18

SEE F

1324636

(SHEET 1 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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UP

FWD

INBD

AFT EQUIPMENT

CENTER - E8

STA

2302.94

RELAYS SHOWN

INSTALLED

A

SEE B THROUGH E

1325448

(SHEET 2 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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RELAY INSTALLATION

FWD

B

UP

FWD

INBD

C

7

5

4

3

5

7

3

6

12 13

11

1325453

(SHEET 3 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281 R1365

4 LOCATIONS

R1366

FWD

FWD

INBD

OUTBD

D

E

16

14

9

8

8

15

12 13

12 13 14

10

10

17

1345377

(SHEET 4 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

UP

FWD

INBD

AFT EQUIPMENT

CENTER - E8

(ALTERNATE CONFIGURATION)

STA

2302.94

RELAYS SHOWN

INSTALLED

F

SEE G THROUGH J

1702058

(SHEET 5 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

RELAY INSTALLATION

FWD

G

UP

FWD

INBD

H

7

5

4

3

5

7

3

6

12 13

11

1702060

(SHEET 6 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: R1365

4 LOCATIONS

R1366

FWD

FWD

INBD

OUTBD

I

J

16

14

9

8

8

15

12 13

12 13 14

10

10

17

1702063

(SHEET 7 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for relay installation on the E-8 shelf. Use the parts 

in Top Kit 015U1808-1.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Open E-8 SHELF - - Gain access to the E-8 shelf.

2 Remove/Keep Static Inverter - - Refer to 747-400 AMM 

24-29-04 as an accepted 

procedure, if Static Inverter is 

installed.

3 Install (New) RELAY BRACKET 

DETAIL

284U4011-45 1 Prepare and apply faying 

surface bond between the 

bottom surface of the bracket 

and the tray, refer to SWPM 

20-20-00 as an accepted 

procedure.

Install (New) BOLT BACS12HN06-7 1 If the bolt can not be installed 

because of a stiffening joggle 

in the equipment tray see Note 

(e).

4 Install (New) BONDING 

JUMPER

BACJ40A20-2 1 Prepare surfaces for bonding 

jumper. Refer to SWPM 

20-20-00 as an accepted 

procedure.

Install (New) SCREW, CAP BACS12GU3K9 1

Install (New) WASHER NAS1149D0316H 4 Install washers in build up as 

shown.

Install (New) NUT BACN10YR3CD 1

5 Install (New) SCREW BACS12HN3-36 1 Install clamps in location, do no 

tighten until after wiring is 

installed.

Install (New) WASHER NAS1149D0332J 2

Install (New) CLAMP, LOOP BACC10GE5 2 Refer to SWPM 20-10-12 as 

an accepted procedure for 

clamp installation.

Install (New) SPACERS FOR 

RIVETS

NAS42DD6-64FC 2

Install (New) NUT BACN10YR3CD 1

6 Install (New) SCREW BACS12GU3K10 1 Back drill hole. Hole diameter 

0.187 - 0.191 inch, refer to 

747-400 SRM 51-40-05 as an 

accepted procedure.

Install (New) WASHER NAS1149D0316H 1

Install (New) NUT BACN10YR3CD 1

(SHEET 8 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

7 Prepare FAY SURFACE 

BOND

- - Prepare surfaces on both sides 

of bracket. Use Cleaning 

Method Type I. Refer to 

SWPM 20-20-00 as an 

accepted procedure.

8 Install (New) RELAY,25A,W/

AUX

BH315 2

9 Install (New) SCREW BACS12GU3K8 4 Install at four locations

Install (New) WASHER NAS1149D0332J 4 Install on near side.

Install (New) WASHER NAS1149D0316H 4 Install on far side.

Install (New) NUT BACN10YR3CD 4

10 Measure RESISTANCE - - (a), (b)

11 Measure RESISTANCE - - (c), (d)

12 Apply SEALANT BMS 5-95 1 Fillet seal all sides of relays 

and between bracket and tray, 

refer to 747-400 AMM 

51-31-01 as an accepted 

procedure.

13 Apply PRIMER BMS 10-11, TYPE 

1

- Touch-up all bare metal 

surfaces and top coat to match 

area color.

14 Install (New) TERMINAL BARR 001-1908-000 4 Install terminal barrier be wire 

installation.

15 Install (New) VINYL MARKER BAC27EEL29698 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

16 Install (New) VINYL MARKER BAC27EEL29699 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

17 Install (New) MARKER BAC27EEL19431 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

18 Install (Kept) Static Inverter 1 Do not install static inverter 

until wiring is completed. Install 

Static Inverter, (if static inverter 

was removed) refer to 747-400 

AMM 24-29-04 as an accepted 

procedure.

19 Close E-8 SHELF - Do not close shelf doors until 

wiring is complete.

(a) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure “Bonding Test for Faying Surfaces” as an 

accepted procedure. Maximum resistance between relay mount and structure, 0.0025 Ohms.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 9 OF 10)
 FIGURE 1: INSTALL RELAYS ON E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

The parts shown in the table below are provided as extra parts for this figure.

(b) If maximum resistance is exceeded, disassemble relay assembly and reassemble making sure both 

relay mounting surface and structure assembly are clean. Refer to SWPM 20-20-00.

(c) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure “Bonding Test for Faying Surfaces” as an 

accepted procedure. Maximum resistance between mounting bracket and structure, 0.003 Ohms.

(d) If maximum resistance is exceeded, disassemble bonding jumper assembly and reassemble bonding 

jumper making sure mounting surfaces are clean. Refer to SWPM 20-20-00 as an accepted procedure.

(e) The existing hole location in the bracket for the bolt may interfere with a stiffening joggle in the 

equipment tray. If this condition exists move the mounting hole in the bracket 1 inch outboard from the 

center of the existing hole and plug existing hole in the bracket. Drill new hole 0.138 - 0.142 inch diameter 

to install the bolt shown Circle Note 3 using additional hardware, washer NAS1149DN616H or equivalent 

and nut BACN10YR06CD or equivalent. 

NAME IDENTIFICATION QTY MORE DATA

Nut BACN10YR3CD 1

Bolt BACS12GU3K10 3

Washer NAS1149D0316H 1

Washer NAS1149D0332J 4

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 10 OF 10)
 FIGURE 2: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 2: WIRE BUNDLE ROUTING INFORMATION

STA

1580

STA

2200

2100

STA

STA

1980

AC1401

W4588

W4488

SEE B

2

SEE A

1

1325695

(SHEET 1 OF 4)
 FIGURE 2: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

ENTRY DOOR

NO. 5L

MAIN

E8 RACK

STA

2340 STA

2320 STA

2300 S-10L

S-11L

S-12L

S-13L

W4488

P180 PANEL

STA 380

FLOOR BEAM

MAWEA

CARDFILE

W4588

W4758

FWD

INBD FWD

A

1

2

B

SEE C

3

1325765

(SHEET 2 OF 4)
 FIGURE 2: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

AP2301

D40103P

(POSITION 15)

STA

2300

STA

2320

W4488

FWD

UP

C

1

1325848

(SHEET 3 OF 4)
 FIGURE 2: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The 

information shown is wire bundle routing for wire bundles W4488, W4455 and used existing wires for wire 

bundle W4758. Install wires. Refer to SWPM 20-10-11 and SWPM 20-10-19 as accepted procedures. For 

wiring changes see applicable figures.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 INSTALL WIRE BUNDLE 

W4488

- - Follow existing wire bundle 

W4488 routing from E-8 shelf, 

disconnect location AP2301 to 

disconnect location AC1401.

2 INSTALL WIRE BUNDLE 

W4588

- - Follow existing wire bundle 

W4588 routing from disconnect 

location AC1401 to P180 Panel 

disconnect location AE0304.

3 INSTALL WIRE BUNDLE 

W4758

- - Use existing wire bundle wiring 

for W4758 routed from P180 

Panel to MAWEA card file.

(SHEET 4 OF 4)
 FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 3: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 1, 8, 10-12; Group 18, Configuration 2; Group 19, Configuration 1; Group 32, 34-

35: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as 

an accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

071-22 W3851

-106

CENTER - AFT

LEFT

47

D43827P

(POS 10)

35 W4488-

AP2301

D40103P

(POS 15)

37

J

E8 EQUIPMENT

W4588

-102

W4488- 085-20 W4588

-102

084-20 46

W4588

(REF) 31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326169

(SHEET 1 OF 1)
 FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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FIGURE 4: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 7: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 5

004-20

W3851

-106

CENTER - AFT

LEFT

47

D43827P

(POS 10)

30 W4488-

AP2301

D40103P

(POS 15)

37

J

E8 EQUIPMENT

W4588

-102

W4488- 085-20 W4588

-102

084-20 46

W4588

(REF)

33

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

071-22 31

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326172

(SHEET 1 OF 1)
 FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 5: INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 4, 14; Group 15, Configuration 2; Group 17, Configuration 2: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

CENTER - AFT

LEFT

W4588

-102

47

D43827P

(POS 10)

W3851

-106

35

AP2301

D40103P

(POS 15)

37

J

W4488-

W4488- 085-20

084-20

E8 EQUIPMENT

46

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

1326174

(SHEET 1 OF 1)
 FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 2, 30-31, 33, 37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

033-18

CENTER - AFT

LEFT

(2 LOCATIONS)

47

D43827P

(POS 10)

35 W4488-

AP2301

D40103P

(POS 15)

W3851

-106

37 W4588

-102 085-20

071-22

W4588

-102

J

E8 EQUIPMENT

W4488-

25

084-20

W4588

(REF)

46

31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326179

(SHEET 1 OF 2)
 FIGURE 6: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 16: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

033-18

CENTER - AFT

LEFT

(2 LOCATIONS)

47

D43827P

(POS 10)

35 W4488-

AP2301

D40103P

(POS 15)

W3851

-106

37 W4588

-102 085-20

071-22 W4588

-102

W4588

-102

J

E8 EQUIPMENT

W4488-

084-20 46

31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326183

(SHEET 1 OF 2)
 FIGURE 7: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 8: INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, Configuration 1; 

Group 20-22; Group 23, Configuration 2; Group 24-31: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

1326188

(SHEET 1 OF 1)
 FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)

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FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 12: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

AEO418

J D40406P

(POS 14)

15

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

113-20

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326195

(SHEET 1 OF 2)
 FIGURE 9: INSTALL NEW WIRING (WIRE BUNDLE W4588)

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3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

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FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 11, 13: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

W4588-

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

AEO418

J D40406P

(POS 14)

15

114-20

J

W4588-

W4588- 149-20

148-20

P180 PANEL-

(2 LOCATIONS)

46

18

113-20

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

4

SPARE

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326249

(SHEET 1 OF 2)
 FIGURE 10: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 8, 14: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J D41805P

(POS 19)

1

W4588- 119-20

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

(2 LOCATIONS)

117-20

2

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

4

SPARE

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326260

(SHEET 1 OF 2)
 FIGURE 11: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

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3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 10: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 5

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J D41805P

(POS 19)

1

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

117-20

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326280

(SHEET 1 OF 2)
 FIGURE 12: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 13: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 17, Configuration 2; Group 19, 

Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-31: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-103, if additional BACC47CP1S socket is required use extra from

-101 or -102 wire kit. Route new wiring following the existing wire bundle routing, refer to SWPM

20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -103 

(W3845)

289U1225-103W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

19

J J

12 18

D41785P D41807P

AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER

DISTRIBUTION

D41786P J

29 2AB-24

13 2AE-24

2AD-24

W3845

28

NC

2AC-24 W4815

(REF)

W4588

-102

(2 LOCATIONS)

(POS 10)

(POS 13)

W4758

-104

3

2

NC

(POS 9)

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326291

(SHEET 1 OF 1)
 FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 14: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4758)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-104. Use existing wiring and follow existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 CONTACT, 

SOCKET

BACC47EG2 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

2 LACING TAPE 289T9001-51 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1

DW3417C

W4758- 634-24

W4758- 633-24

M7952

19

MAWEA CARD

FILE (P54)

18

J D41807P

PANEL-DC POWER

DISTRIBUTION

AE0304

FUEL CMD

P180 (POS 13)

(2 LOCATIONS)

W3845

-103

2

FUEL CMD

STAB L

STAB R

C9

C8

REFERENCE: 747 WIRING DIAGRAM 30-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326308

(SHEET 1 OF 1)
 FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: 

1 7

23

196-20

332-12B

W3851

C1 C2

A1

D40107P J

1

194-20

336-12Y

W4601

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-LEFT

C2

R7401 RLY

E8 EQUIPMENT CENTER - LEFT AFT

15

19

054-20

B1 B2

A2

AP2301

334-12R

B1

A1

X2

H.S. PUMP

CONT-LEFT

R1365 RLY

B2

A2

335-12B

(3 LOCATIONS)

X1

5

3

2

(5 LOCATIONS)

195-20

333-12Y

331-12R

319-12R

320-12B

321-12Y

4

(6 LOCATIONS)

X1

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-28

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326327

(SHEET 1 OF 2)
 FIGURE 15: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, 

SOCKET

BACC47CP1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary, see kit of parts for Figure 13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-LEFT

R7401 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

197-20

604-20

(3 LOCATIONS)

H.S. PUMP

CONT-LEFT

R1365 RELAY

12

NC 13

14 NC

D40103P

AP2301

11

NC

13

12

37

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326337

(SHEET 1 OF 2)
 FIGURE 16: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

1 4

198-20 11

600-20

H.S. PUMP

CONT-LEFT

R7401 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

J

W4601

(REF)

D40107P

H.S. PUMP

CONT-LEFT

R1365 RELAY

12

NC 13 14 NC

11

NC 13

12

14 NC

064-20

AP2301

SM14

W3851

4

X1

X2

(2 LOCATIONS)

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326351

(SHEET 1 OF 2)
 FIGURE 17: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an 

accepted procedure.

3 SPLICE D436-38 1 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20, 22; Group 23, Configuration 2; Group 24-25, 28, 32-36: 

1 7

3

1

602-20

341-12B

2

W3851

C1 C2

A1

D40106P J

5

603-20

339-12Y

W4602

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-RIGHT

C2

R7402 RLY

E8 EQUIPMENT CENTER - LEFT AFT

3

2

037-20

B1 B2

A2

X1

AP2301

337-12R

B1

A1

X2

H.S. PUMP

CONT-RIGHT

R1366 RLY

B2

A2

338-12B

(3 LOCATIONS)

X1

5

(5 LOCATIONS)

199-20

342-12Y

340-12R

322-12R

323-12B

324-12Y

4

(6 LOCATIONS)

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327151

(SHEET 1 OF 2)
 FIGURE 18: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 19: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 3, Configuration 1; Group 7, 20-22, 29: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

192-20

193-20

(3 LOCATIONS)

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13

14 NC

D40103P

AP2301

11

NC 13

12

30

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326367

(SHEET 1 OF 1)
 FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 20: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2, 4, 8, 10-12, 14; Group 15, Configuration 2; Group 16; Group 17, Configuration 

2; Group 18, Configuration 2; Group 19, Configuration 1; Group 30-35, 37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

192-20

193-20

(3 LOCATIONS)

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13

14 NC

D40103P

AP2301

11

NC 13

12

35

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326379

(SHEET 1 OF 1)
 FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

1 4

191-20 11

601-20

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

J

W4602

(REF)

D40106P

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13 14 NC

11

NC 13

12

14 NC

063-20

AP2301

SM13

W3851

4

X1

X2

(2 LOCATIONS)

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1326390

(SHEET 1 OF 2)
 FIGURE 21: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 125 of 182

BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an 

accepted procedure.

3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as 

an accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 22: INSTALL RELAYS ON E-8 SHELF

UP

FWD

INBD

AFT E/E

EQUIPMENT CENTER

ENTRY

DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT

CENTER - E8

STA

2302.94

STA

2302.94

INBD FWD

SEE A

1

2

19

18

1345395

(SHEET 1 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

UP

FWD

INBD

AFT EQUIPMENT

CENTER - E8

STA

2302.94

RELAYS SHOWN

INSTALLED SEE B C D

A

E

1345396

(SHEET 2 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

RELAY INSTALLATION

FWD

B

UP

FWD

INBD

C

7

5

4

3

5

7

3

6

12 13

11

1345397

(SHEET 3 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

R1365

4 LOCATIONS

R1366

FWD

FWD

INBD

OUTBD

D

E

9

8

8

10

10

16

14

15

12 13

12 13 14

17

1345398

(SHEET 4 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The QTY 

numbers shown below are the number of parts necessary for this figure. For relay installation on E-8 shelf use 

parts in Top Kit 015U1808-2.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Open E-8 SHELF - - Gain access to the E-8 shelf.

2 Remove/Keep Static Inverter - - Refer to 747-400 AMM 

24-29-04 as an accepted 

procedure.

3 Install (New) RELAY BRACKET 

DETAIL

284U4011-45 1 Prepare and apply faying 

surface bond between the 

bottom surface of the bracket 

and the tray, refer to SWPM 

20-20-00 as an accepted 

procedure.

Install (New) BOLT BACS12HN06-7 1

4 Install (New) BONDING 

JUMPER

BACJ40A20-2 1 Prepare surfaces for bonding 

jumper. Refer to SWPM 

20-20-00 as an accepted 

procedure.

Install (New) SCREW, CAP BACS12GU3K9 1

Install (New) WASHER NAS1149D0316H 4 Install washers in build up as 

shown.

Install (New) NUT BACN10YR3CD 1

5 Install (New) SCREW BACS12HN3-36 1 Install clamps in location, do no 

tighten until after wiring is 

installed.

Install (New) WASHER NAS1149D0332J 2

Install (New) CLAMP, LOOP BACC10GE5 2

Install (New) SPACERS FOR 

RIVETS

NAS42DD6-64FC 2

Install (New) NUT BACN10YR3CD 1

6 Install (New) SCREW BACS12GU3K10 1 Back drill hole, for hole 

diameter, refer to 747-400 

SRM 51-40-05 as an accepted 

procedure.

Install (New) WASHER NAS1149D0316H 1

Install (New) NUT BACN10YR3CD 1

7 Prepare FAY SURFACE 

BOND

- - Prepare surfaces on both sides 

of bracket. Use Cleaning 

Method Type I. Refer to 

SWPM 20-20-00.

8 Install (New) RELAY,25A,W/

AUX

BH315 2

(SHEET 5 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

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9 Install (New) SCREW BACS12GU3K8 4 Install four locations

Install (New) WASHER NAS1149D0332J 4 Install on near side.

Install (New) WASHER NAS1149D0316H 4 Install on far side.

Install (New) NUT BACN10YR3CD 4

10 Measure RESISTANCE - - (a), (b)

11 Measure RESISTANCE - - (c), (d)

12 Apply SEALANT BMS 5-95 1 Fillet seal all sides of relays 

and between bracket and tray, 

refer to 747-400 AMM 

51-31-01 as an accepted 

procedure.

13 Apply PRIMER BMS 10-11, TYPE 

1

- Touch-up all bare metal 

surfaces and top coat to match 

area color.

14 Install (New) TERMINAL BARR 001-1908-000 4 Install terminal barrier be wire 

installation.

15 Install (New) VINYL MARKER BAC27EEL29698 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

16 Install (New) VINYL MARKER BAC27EEL29699 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

17 Install (New) MARKER BAC27EEL19431 1 For Vinyl Marker installation, 

Refer to 747-400 AMM 

20-11-16 as an accepted 

procedure.

18 Install (Kept) Static Inverter - 1 Do not install Static Inverter 

until wiring is completed. 

Install Static Inverter, refer to 

747-400 AMM 24-29-04 as an 

accepted procedure.

19 Close E-8 SHELF - - Do not close shelf doors until 

wiring is complete.

(a) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure "Bonding Test for Faying Surfaces" as an 

accepted procedure. Maximum resistance between relay mount and structure, 0.0025 Ohms.

(b) If maximum resistance is exceeded, disassemble relay assembly and reassemble making sure both 

relay mounting surface and structure assembly are clean. Refer to SWPM 20-20-00.

(c) Use Bonding Meter. Refer to SWPM 20-20-00 Procedure "Bonding Test for Faying Surfaces" as an 

accepted procedure. Maximum resistance between mounting bracket and structure, 0.003 Ohms.

(d) If maximum resistance is exceeded, disassemble bonding jumper assembly and reassemble bonding 

jumper making sure mounting surfaces are clean. Refer to SWPM 20-20-00

STEP TASK NAME IDENTIFICATION QTY MORE DATA

(SHEET 6 OF 7)
 FIGURE 22: INSTALL RELAYS ON E-8 SHELF

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The parts shown in the table below are provided as extra parts for this figure.

NAME IDENTIFICATION QTY MORE DATA

Bolt BACN10YR3CD 1

Bolt BACS12GU3K10 3

Washer NAS1149D0316H 1

Washer NAS1149D0332J 4

(SHEET 7 OF 7)
 FIGURE 23: WIRE BUNDLE ROUTING INFORMATION

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FIGURE 23: WIRE BUNDLE ROUTING INFORMATION

STA

1580

STA

2200

2100

STA

STA

1980

AC1401

W4588

W4488

SEE B

2

SEE A

1

1326410

(SHEET 1 OF 4)
 FIGURE 23: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

E8 RACK

STA

2340 STA

2320 STA

2300 S-10L

S-11L

S-12L

S-13L

W4488

ENTRY DOOR

NO. 5L

MAIN

P180 PANEL

STA 380

FLOOR BEAM

MAWEA

CARDFILE

W4588

W4758

FWD

INBD FWD

A

1

SEE C

2

B

3

1326411

(SHEET 2 OF 4)
 FIGURE 23: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

AP2301

D40103P

(POSITION 15)

STA

2300

STA

2320

W4488

FWD

UP

C

1

1327097

(SHEET 3 OF 4)
 FIGURE 23: WIRE BUNDLE ROUTING INFORMATION

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BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The 

information shown is wire bundle routing for wire bundles W4488, W4455, refer to SWPM 20-10-11. For wiring 

changes see applicable figures.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 INSTALL WIRE BUNDLE 

W4488

- - Follow existing wire bundle 

W4488 routing from E-8 shelf, 

disconnect location AP2301 to 

disconnect location AC1401.

2 INSTALL WIRE BUNDLE 

W4588

- - Follow existing wire bundle 

W4588 routing from disconnect 

location AC1401 to P180 Panel 

disconnect location AE0304.

3 INSTALL WIRE BUNDLE 

W4758

- - Follow existing wire bundle 

W4758 routing from P180 

Panel disconnect location 

AE0304 to MAWEA card file.

(SHEET 4 OF 4)
 FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

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FIGURE 24: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

071-22 W3851

-106

CENTER - AFT

LEFT

47

D43827P

(POS 10)

35 W4488-

AP2301

D40103P

(POS 15)

37

J

E8 EQUIPMENT

W4588

-102

W4488- 085-20 W4588

-102

084-20 46

W4588

(REF) 31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327108

(SHEET 1 OF 1)
 FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588)

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FIGURE 25: INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

24 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

3

2

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

1327109

(SHEET 1 OF 1)
 FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)

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FIGURE 26: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W3845)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-103, if additional BACC47CP1S socket is required use extra from

-101 or -102 wire kit. Route new wiring following the existing wire bundle routing, refer to SWPM

20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -103 

(W3845)

289U1225-103W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

19

J J

12 18

D41785P D41807P

AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER

DISTRIBUTION

D41786P J

29 2AB-24

13 2AE-24

2AD-24

W3845

28

NC

2AC-24 W4815

(REF)

W4588

-102

(2 LOCATIONS)

(POS 10)

(POS 13)

W4758

-105

3

2

NC

(POS 9)

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327113

(SHEET 1 OF 1)
 FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758)

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FIGURE 27: INSTALL NEW WIRING (WIRE BUNDLE W4758)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-105. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -105 

(W4758)

289U1225-105W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47EG2 4 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 LACING TAPE 289T9001-51 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 3

DW3417C

C9

W4758-

W4758-

M7952

19 C8

MAWEA CARD

FILE (P54)

18

J D41807P

PANEL-DC POWER

DISTRIBUTION

AE0304

FUEL CMD

STAB L

P180 (POS 13)

(4 LOCATIONS)

W3845

-103

634-24

633-24

2

FUEL CMD

STAB R

REFERENCE: 747 WIRING DIAGRAM 30-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327119

(SHEET 1 OF 1)
 FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

1 7

23

196-20

332-12B

W3851

C1 C2

A1

D40107P J

1

194-20

336-12Y

W4601

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-LEFT

C2

R7401 RLY

E8 EQUIPMENT CENTER - LEFT AFT

15

19

054-20

B1 B2

A2

AP2301

334-12R

B1

A1

X2

H.S. PUMP

CONT-LEFT

R1365 RLY

B2

A2

335-12B

(3 LOCATIONS)

X1

5

3

2

(5 LOCATIONS)

195-20

333-12Y

331-12R

319-12R

320-12B

321-12Y

4

(6 LOCATIONS)

X1

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-28

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327125

(SHEET 1 OF 2)
 FIGURE 28: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary, see kit of parts for Figure 26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, 

SOCKET

BACC47CP1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 29: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as 

an accepted procedure.

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-LEFT

R7401 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

197-20

604-20

(3 LOCATIONS)

H.S. PUMP

CONT-LEFT

R1365 RELAY

12

NC 13

14 NC

D40103P

AP2301

11

NC

13

12

37

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327130

(SHEET 1 OF 1)
 FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

1 4

198-20 11

600-20

H.S. PUMP

CONT-LEFT

R7401 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

J

W4601

(REF)

D40107P

H.S. PUMP

CONT-LEFT

R1365 RELAY

12

NC 13 14 NC

11

NC 13

12

14 NC

064-20

AP2301

SM14

W3851

4

X1

X2

(2 LOCATIONS)

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327132

(SHEET 1 OF 2)
 FIGURE 30: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an 

accepted procedure.

3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as 

an accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

1 7

3

1

602-20

341-12B

2 W3851

C1 C2

A1

D40106P J

5

603-20

339-12Y

W4602

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-RIGHT

C2

R7402 RLY

E8 EQUIPMENT CENTER - LEFT AFT

3

2

037-20

B1 B2

A2

X1

AP2301

337-12R

B1

A1

X2

H.S. PUMP

CONT-RIGHT

R1366 RLY

B2

A2

338-12B

(3 LOCATIONS)

X1

5

(5 LOCATIONS)

199-20

342-12Y

340-12R

322-12R

323-12B

324-12Y

4

(6 LOCATIONS)

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327154

(SHEET 1 OF 2)
 FIGURE 31: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 32: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

192-20

193-20

(3 LOCATIONS)

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13 14 NC

D40103P

AP2301

11

NC 13

12

35

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327159

(SHEET 1 OF 1)
 FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 9: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

1 4

191-20 11

601-20

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

J

W4602

(REF)

D40106P

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13 14 NC

11

NC 13

12

14 NC

063-20

AP2301

SM13

W3851

4

X1

X2

(2 LOCATIONS)

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1327163

(SHEET 1 OF 2)
 FIGURE 33: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

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NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

26 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 TERMINAL LUG BACT12AC2 2 Refer to SWPM 20-30-11 as an 

accepted procedure.

3 SPLICE D436-38 1 Refer to SWPM 20-30-12 as 

an accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF

UP

FWD

INBD

ENTRY

DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT

CENTER - E8

STA

2302.94

AFT E/E

EQUIPMENT CENTER

STA

2302.94

INBD FWD

SEE A

1343104

(SHEET 1 OF 3)
 FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

AP2301

W3851

R1365

R1366

R7402

R7401

4 LOCATIONS

EXISTING 

CLAMP

UP

FWD

INBD

A

6

5

4

3

2

1

2

1343075

(SHEET 2 OF 3)
 FIGURE 34: WIRE BUNDLE ROUTING E-8 SHELF

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The 

information shown is wire bundle routing for W3851. Install new wires. Refer to SWPM 20-10-11 and SWPM 

20-10-19 as accepted procedures. For wiring changes see applicable figures.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove CLAMPS - Remove clamps as necessary 

for routing new wires and 

removal of old wires.

2 Install (New) ASSY -106 

(W3851)

1 Follow existing wire bundle 

W3851 routing on E-8 shelf.

3 Install (New) BOLT BACS12HN3-8 1

Install (New) WASHER NAS1149D0332J 1

Install (New) CLAMP, LOOP BACC10GE5 1

4 Tighten Clamps - 1 Tighten bolt after wiring is 

installed in clamp.

5 Install (New) BOLT BACS12HN3-20 1

Install (New) WASHER NAS1149D0332J 1

Install (New) CLAMP, LOOP BACC10GE10 1

Install (New) SPACERS FOR 

RIVETS

NAS42DD6-64FC 1

6 INSTALL Clamps - Install existing clamps.

(SHEET 3 OF 3)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

A

P180 PANEL

FOR WIRE BUNDLE

ROUTING INFORMATION

STA 380

FLOOR BEAM

MAWEA

CARDFILE W4588

W4758

FWD

SEE A THROUGH F

2

B

1

1343077

(SHEET 1 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

A

STA

380

W4758

W4588

S-39

FWD

A

SEE B

1

2

P180

1343126

(SHEET 2 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

A

B

STA

400

RBL

100

RBL

50

W4758

FWD

BULKHEAD

B

1343138

(SHEET 3 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

B

STA400

W4758

D

FWD

C

1343186

(SHEET 4 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

D

E

W4758

W4758

STA420

STA460

FWD

D

1343192

(SHEET 5 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

E

F

STA

380

W4758

FWD

E

1

1343194

(SHEET 6 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 9: 

F

STA

380

W4758

STA

360

RBL

20

FWD

F

MAWAE CARD FILE

1

1343195

(SHEET 7 OF 8)
 FIGURE 35: WIRE BUNDLE ROUTING P180 PANEL TO MAWEA CARD FILE

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The 

information shown is wire bundle routing for W4758. Install new wires. Refer to SWPM 20-10-11 and SWPM 

20-10-19 as accepted procedures. For wiring changes see applicable figure.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 ROUTING WIRE BUNDLE 289U1225-105W 1 Follow existing wire bundle 

W4758 routing from P180 

panel to MAWEA card file.

2 ROUTING WIRE BUNDLE - 1 Follow existing wire bundle 

W4588 routing from 

Disconnect location AC1401 

to P180 panel, disconnect 

location AE0304.

(SHEET 8 OF 8)
 FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF

UP

FWD

INBD

ENTRY

DOOR

NO. 5L

MAIN

E8 RACK

AFT EQUIPMENT

CENTER - E8

STA

2302.94

AFT E/E

EQUIPMENT CENTER

STA

2302.94

INBD FWD

SEE A

1345408

(SHEET 1 OF 3)
 FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF

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BOEING SERVICE BULLETIN 747-28A2281

This Figure applies to Group 1-2; Group 3, Configuration 1; Group 4; Group 5, Configuration 2; Group 6, 

Configuration 2; Group 7-8, 10-14; Group 15, Configuration 2; Group 16; Group 17, Configuration 2; Group 18, 

Configuration 2; Group 19, Configuration 1; Group 20-22; Group 23, Configuration 2; Group 24-37: 

AP2301

W3851

R1365

R1366

R7402

R7401

4 LOCATIONS

EXISTING 

CLAMP

UP

FWD

INBD

A

6

5

4

3

2

1

2

1345409

(SHEET 2 OF 3)
 FIGURE 36: WIRE BUNDLE ROUTING E-8 SHELF

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 164 of 182

BOEING SERVICE BULLETIN 747-28A2281

The step numbers shown below agree with the numbers shown in the circle symbols in the figure. The 

information shown is wire bundle routing for W3851. Install new wires. Refer to SWPM 20-10-11 and SWPM 

20-10-19 as accepted procedures. For wiring changes see applicable figures.

STEP TASK NAME IDENTIFICATION QTY MORE DATA

1 Remove CLAMPS - Remove clamps as necessary 

for routing new wires and 

removal of old wires.

2 Install (New) ASSY -106 

(W3851)

1 Follow existing wire bundle 

W3851 routing on E-8 shelf.

3 Install (New) BOLT BACS12HN3-8 1 For some installation a 

Install (New) WASHER NAS1149D0332J 1

Install (New) CLAMP, LOOP BACC10GE5 1

4 Tighten Clamps - 1 Tighten bolt after wiring is 

installed in clamp.

5 Install (New) BOLT BACS12HN3-20 1

Install (New) WASHER NAS1149D0332J 1

Install (New) CLAMP, LOOP BACC10GE10 1

Install (New) SPACERS FOR 

RIVETS

NAS42DD6-64FC 1

6 INSTALL Clamps - Install existing clamps.

(SHEET 3 OF 3)
 FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 37: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 20, 29: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as 

an accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer toSWPM 20-61-11 an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

071-22 W3851

-106

CENTER - AFT

LEFT

47

D43827P

(POS 10)

30 W4488-

AP2301

D40103P

(POS 15)

37

J

E8 EQUIPMENT

W4588

-102

W4488- 085-20 W4588

-102

084-20 46

W4588

(REF) 31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

1 5

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566752

(SHEET 1 OF 1)
 FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 38: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 6, Configuration 2; Group 23, Configuration 2; Group 24: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19 as an accepted procedure. Use lacing tape as

necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

36

070-22 30

1 5

W3851

-106

CENTER - AFT

LEFT

47

D43827P

(POS 10)

W4488-

AP2301

D40103P

(POS 15)

37

J

E8 EQUIPMENT

W4588

-102

W4488- 085-20 W4588

-102

084-20 46

W4588

(REF)

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566763

(SHEET 1 OF 1)
 FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 3, Configuration 1; Group 21-22: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

30

004-20 33

1 5

CENTER - AFT

LEFT

(2 LOCATIONS)

47

D43827P

(POS 10)

W4488-

AP2301

D40103P

(POS 15)

W3851

-106

37 W4588

-102 085-20

071-22

W4588

-102

J

E8 EQUIPMENT

W4488-

084-20

W4588

(REF)

46

31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566776

(SHEET 1 OF 2)
 FIGURE 39: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

This Figure applies to Group 5, Configuration 2; Group 13, 25-28, 36: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-101. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -101 

(W4488)

289U1225-101W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

36

070-22 30

1 5

CENTER - AFT

LEFT

(2 LOCATIONS)

47

D43827P

(POS 10)

W4488-

AP2301

D40103P

(POS 15)

W3851

-106

37 W4588

-102 085-20

071-22

W4588

-102

J

E8 EQUIPMENT

W4488-

084-20

W4588

(REF)

46

31

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

2

3

4

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566796

(SHEET 1 OF 2)
 FIGURE 40: REWORK / INSTALL NEW WIRING (WIRE BUNDLE W4488)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 19, Configuration 1; Group 21, 26-27, 29-31, 37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

320-12B

1 7

23

196-20

332-12B

W3851

C1 C2

A1

D40107P J

1

194-20

336-12Y

W4601

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-LEFT

C2

R7401 RLY

E8 EQUIPMENT CENTER - LEFT AFT

15

19

054-20

B1 B2

A2

AP2301

334-12R

B1

A1

X2

H.S. PUMP

CONT-LEFT

R1365 RLY

B2

A2

335-12B

(3 LOCATIONS)

X1

5

3

2

(5 LOCATIONS)

195-20

333-12Y

331-12R

319-12R

321-12Y

4

(6 LOCATIONS)

X1

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-28

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566856

(SHEET 1 OF 2)
 FIGURE 41: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, 

SOCKET

BACC47CP1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

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BOEING SERVICE BULLETIN 747-28A2281

FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

This Figure applies to Group 21, 26-27, 29-31, 37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

323-12B

1 7

3

1

602-20

341-12B

2

W3851

C1 C2

A1

D40106P J

5

603-20

339-12Y

W4602

(REF)

C1

W2018

(REF)

X2

H.S. PUMP

CONT-RIGHT

C2

R7402 RLY

E8 EQUIPMENT CENTER - LEFT AFT

3

2

037-20

B1 B2

A2

X1

AP2301

337-12R

B1

A1

X2

H.S. PUMP

CONT-RIGHT

R1366 RLY

B2

A2

338-12B

(3 LOCATIONS)

X1

5

(5 LOCATIONS)

199-20

342-12Y

340-12R

322-12R

324-12Y

4

(6 LOCATIONS)

6 (3 LOCATIONS)

REFERENCE: 747 WIRING DIAGRAM 28-21-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566867

(SHEET 1 OF 2)
 FIGURE 42: REWORK / INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE W3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 174 of 182

BOEING SERVICE BULLETIN 747-28A2281

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT BACC47CP3T 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 CONTACT BACC47CP3T 3 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 TERMINAL LUG BACT12E10 6 Refer to SWPM 20-30-11 as an 

accepted procedure.

5 TERMINAL LUG BACT12AC2 5 Refer to SWPM 20-30-11 as an 

accepted procedure.

6 TERMINAL LUG BACT12AC12 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

7 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

(SHEET 2 OF 2)
 FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 175 of 182

BOEING SERVICE BULLETIN 747-28A2281

FIGURE 43: INSTALL NEW WIRING ON E8 SHELF (WIRE BUNDLE 3851)

This Figure applies to Group 5, Configuration 2; Group 6, Configuration 2; Group 13; Group 23, Configuration 

2; Group 24-28, 36: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-106. Route new wiring following the existing wire bundle routing,

refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing tape as necessary, see kit of parts for Figure

13 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -106 

(W3851)

289U1225-106W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONTACT, PIN BACC47CN1S 1 Refer to SWPM 20-61-11 as an 

accepted procedure.

3 TERMINAL LUG BACT12AC2 3 Refer to SWPM 20-30-11 as an 

accepted procedure.

4 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

36

1 4

W4488

-101

W3851

11

H.S. PUMP

CONT-RIGHT

R7402 RELAY

E8 EQUIPMENT CENTER - LEFT AFT

192-20

193-20

(3 LOCATIONS)

H.S. PUMP

CONT-RIGHT

R1366 RELAY

12

NC 13

14 NC

D40103P

AP2301

11

NC 13

12

14 NC

J

2

3

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1566869

(SHEET 1 OF 1)
 FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 176 of 182

BOEING SERVICE BULLETIN 747-28A2281

FIGURE 44: INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 18, Configuration 2; Group 32-33, 36-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102 and supplemental kit 015U1808-3. Route new wiring

following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing

tape as necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONNECTOR, 

PLUG

BACC45FT16-

24P6

1 New connector supplied in 

015U1808-3 supplemental kit. 

Refer to SWPM 20-60-06 as 

an accepted procedure.

3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

6 ID. Tape 289U1225-10801 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 5

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

4

3

2 6

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

1743637

(SHEET 1 OF 1)
 FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 177 of 182

BOEING SERVICE BULLETIN 747-28A2281

FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 16, 35: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102 and supplemental kit 015U1808-3. Route new wiring

following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing

tape as necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONNECTOR, 

PLUG

BACC45FT16-

24P6

1 New connector supplied in 

supplemental kit 015U1808-3. 

Refer to SWPM 20-60-06 as 

an accepted procedure.

3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 6

W4588-

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

AEO418

J D40406P

(POS 14)

15

114-20

J

W4588-

W4588- 149-20

148-20

P180 PANEL-

(2 LOCATIONS)

46

18

113-20

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

4

3

5

SPARE

2 7

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1743638

(SHEET 1 OF 2)
 FIGURE 45: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 178 of 182

BOEING SERVICE BULLETIN 747-28A2281

4 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

5 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

6 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

7 ID.TAPE 289U1225-10801 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 179 of 182

BOEING SERVICE BULLETIN 747-28A2281

FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

This Figure applies to Group 34: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-102 and supplemental kit 015U1808-3. Route new wiring

following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19. Use lacing

tape as necessary, see kit of parts for Figure 3 for lacing tape.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -102 

(W4588)

289U1225-102W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

2 CONNECTOR, 

PLUG

BACC45FT16-

24P6

1 New connector supplied in 

supplemental kit 015U1808-3. 

Refer to SWPM 20-60-06 as 

an accepted procedure.

3 CONTACT, PIN BACC47CN1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

1 6

DC POWER

DISTRIBUTION

W4488

-101

47

D43827P

(POS 10)

W3845

-103

12

AE0304

D41785P

(POS 9)

13

J D41805P

(POS 19)

1

W4588- 119-20

J

W4588-

W4588- 149-20

148-20

P180 PANEL46

(2 LOCATIONS)

117-20

2

SPARE

W4588-

(2 LOCATIONS)

(2 LOCATIONS)

J

AC1401

4

3

5

SPARE

2 7

REFERENCE: 747 WIRING DIAGRAM 28-42-15

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1743639

(SHEET 1 OF 2)
 FIGURE 46: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W4588)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 180 of 182

BOEING SERVICE BULLETIN 747-28A2281

4 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

5 INSULATION 

SLEEVING, HEAT 

SHRINKABLE, 

POLYOLEFIN, 

FLEXIBLE, X-LI

M23053/5-107-4 2 Refer to SWPM 20-10-11 as an 

accepted procedure.

6 LACING TAPE 289T9001-21 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

7 ID. TAPE 289U1225-10801 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)
 FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 181 of 182

BOEING SERVICE BULLETIN 747-28A2281

FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)

This Figure applies to Group 16; Group 18, Configuration 2; Group 32-37: 

The flag note numbers shown below agree with the numbers shown in the flag symbols in the figure.

NOTE: Use the parts from wire kit 289U1225-103 and supplemental kit 015U1808-3. Route new wiring

following the existing wire bundle routing, refer to SWPM 20-10-11 and SWPM 20-10-19 as an

accepted procedure. Use lacing tape as necessary.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

1 ASSY -103 

(W3845)

289U1225-103W 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

1 5

19

J J

12 18

D41785P D41807P

AE0304 AE0304

(2 LOCATIONS)

P180 PANEL-DC POWER

DISTRIBUTION

D41786P J

29 2AB-24

13 2AE-24

2AD-24

W3845

28

NC

2AC-24 W4815

(REF)

W4588

-102

(2 LOCATIONS)

(POS 10)

(POS 13)

W4758

-104

4

3

NC

(POS 9)

2 6

REFERENCE: 747 WIRING DIAGRAM 28-42-15, 30-41-31

ADDED WIRE OR NEW ROUTING

EXISTING WIRE

DELETED WIRE OR FORMER ROUTING

1743636

(SHEET 1 OF 2)
 FIGURE 47: REWORK/INSTALL NEW WIRING (WIRE BUNDLE W3845)

Original Issue: December 13, 2007

Revision 1: November 25, 2009 747-28A2281

BOEING PROPRIETARY - Copyright © Unpublished Work - See page 1 for details. 182 of 182

BOEING SERVICE BULLETIN 747-28A2281

2 CONNECTOR, 

RECEPTACLE

BACC45FN16-

24S6

1 New connector supplied in 

supplemental kit 015U1808-3. 

Refer to SWPM 20-60-06 as 

an accepted procedure.

SCREW BACS12HN04U6 2 Hardware to install connector.

WASHER NAS1149DN332J 2

NUT BACN10JC04CM 2

3 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

4 CONTACT, 

SOCKET

BACC47CP1S 2 Refer to SWPM 20-61-11 as an 

accepted procedure.

5 LACING TAPE 289T9001-91 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

6 ID. TAPE 289U1225-10701 1 Refer to SWPM 20-10-11 as an 

accepted procedure.

FLAG 

NOTE NAME IDENTIFICATION QTY MORE DATA

(SHEET 2 OF 2)